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CFR Citation: 14 CFR Part 39

Docket ID: [Docket No. 2003-CE-67-AD; Amendment 39-13878; AD 2004-24-02]

RIN ID: RIN 2120-AA64

NOTICE: RULES

ACTION: Airworthiness directives:

DOCUMENT ACTION: Final rule.

SUBJECT CATEGORY: Airworthiness Directives; Ostmecklenburgische Flugzeugbau GmbH ModelOMF-100-160 Airplanes

DATES: This AD becomes effective on December 28, 2004.

As of December 28, 2004, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation.

DOCUMENT SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain Ostmecklenburgische Flugzeugbau GmbH (OMF) Model OMF100160 airplanes. This AD requires you to inspect the outside tube (cage) that supports the main landing gear leg for cracks, repair if cracks are found, and inspect the thickness of the tube if no cracks were found and reinforce the tube as necessary. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect, correct, and prevent future cracks in the outside tube of the main landing gear leg, which could result in structural failure of the fuselage tubing assembly. This failure could lead to loss of control of the airplane.

SUMMARY: Ostmecklenburgische Flugzeugbau GmbH,

SUPPLEMENTAL INFORMATION

What events have caused this AD? The LuftfahrtBundesamt (LBA), which is the airworthiness authority for Germany, recently notified the FAA that an unsafe condition may exist on certain OMF Model OMF100160 airplanes. The LBA reports that the manufacturer received a report of cracks in the outside fuselage tube that supports the main landing gear leg. Further investigation revealed that one manufacturer of fuselage tubes used outofdesign dimensions for the tube elements.

What is the potential impact if FAA took no action? Cracks in the outside tube of the main landing gear leg, if not detected, corrected, and prevented, could result in structural failure of the fuselage tubing assembly. This failure could lead to loss of control of the airplane.

Has FAA taken any action to this point? We issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to certain OMF Model OMF100160 airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on August 18, 2004, (69 FR 51206). The NPRM proposed to detect, correct, and prevent future cracks in the outside tube of the main landing gear leg. These cracks could result in structural failure of the fuselage tubing assembly and lead to loss of control of the airplane.

Comments

Was the public invited to comment? We provided the public the opportunity to participate in developing this AD. We received no comments on the proposal or on the determination of the cost to the public.

Conclusion

What is FAA's final determination on this issue? We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial corrections. We have determined that these minor corrections: Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was already proposed in the NPRM.

Changes to 14 CFR Part 39Effect on the AD

How does the revision to 14 CFR part 39 affect this AD? On July 10, 2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs the FAA's AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions.

Costs of Compliance

How many airplanes does this AD impact? We estimate that this AD affects 11 airplanes in the U.S. registry.

What is the cost impact of this AD on owners/operators of the affected airplanes? We estimate the following costs to accomplish the inspections:
Total cost
Labor cost Parts cost per Total cost on airplane U.S. operators Inspection for cracks2 N/A $130 $1,430. workhours est. $65 per hour
= $130.
Inspection for inadequate N/A 130 OMF will cover thickness of tubing that the cost for supports the main landing the special gear leg2 workhours est. inspection. $65 per hour = $130.

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We estimate the following costs to accomplish any necessary repairs that would be required based on the results of these proposed inspections. We have no way of determining the number of airplanes that may need this repair:
Total cost per Labor cost Parts cost airplane 85 workhours x $65 per hour = $5,525....... None per manufacturer............................. $5,525 Regulatory Findings

Will this AD impact various entities? We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.

Will this AD involve a significant rule or regulatory action? For the reasons discussed above, I certify that this AD:

1. Is not a ``significant regulatory action'' under Executive Order 12866;

2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and

3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ``Docket No. 2004CE67AD'' in your request.

This rulemaking is promulgated under the authority in Subtitle VII, Part A, Subpart III, Section 44701, General requirements. Under that section, the FAA is charged with prescribing minimum standards required in the interest of safety for the design of aircraft. This regulation is within the scope of that authority since it corrects an unsafe condition in the design of the aircraft caused by cracks in the outside tube of the main landing gear leg.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. FAA amends Sec. 39.13 by adding a new AD to read as follows: 20042402 Ostmecklenburgische Flugzeugbau GmbH: Amendment 3913878; Docket No. 2004CE67AD.
When Does This AD Become Effective?
(a) This AD becomes effective on December 28, 2004.
What Other ADs Are Affected by This Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects Model OMF100160 airplanes, serial numbers 0006, 0007, 0012 through 0015, 0017, 0018, 0020, 0021, 0024, 0025, 0028, and 0029; that are certificated in any category.
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of cracks in the fuselage tubing assembly and inadequate thickness of tubing that supports the main landing gear leg. The actions specified in this AD are intended to detect, correct, and prevent future cracks in the tubing for the main landing gear leg, which could result in failure of the fuselage tubing assembly. This failure could lead to loss of control of the airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following: Actions Compliance Procedures (1) Inspect the main landing Inspect the airplane Inspect following gear leg support for cracks. within 50 hours the procedures in timeinservice OMF Alert Service (TIS) after Bulletin No. 1107/ December 28, 2004 0002, dated (the effective date September 16, 2003. of this AD).
(2) If cracks are found Repair prior to Contact an during any inspection further flight Ostmecklengurgische required in paragraph after the Flugzeugbau GmbH (e)(1) or (e)(3)(ii) of inspection where (OMF)
this AD, obtain repair cracks are found. representative at 1 instructions from the 8193771177 for manufacturer through the repair instructions FAA and incorporate the and incorporate repair instructions. This these instructions. repair eliminates the Summarize and copy repetitive inspection all correspondence requirement of this AD. and send to FAA at the address specified in paragraph (f) of this AD. (3) If no cracks are found Inspect for tubing Inspect following during the inspection thickness of the procedures in OMF required in paragraph airplane within 50 Alert Service (e)(1) of this AD, do the hours TIS after the Bulletin No. 1107/ following: initial inspection 0002, dated (i) inspect tubing for required in September 16, 2003. proper thickness and make paragraph (e)(1) of Reinforce with any appropriate this AD. Reinforce instructions from reinforcements prior to further the manufacturer. (ii) repetitively inspect flight after the Contact an main landing gear leg inspection required Ostmecklengurgische support for cracks in paragraph Flugzeugbau GmbH (e)(3)(i) of this (OMF)
AD. Repetitively representative at 1 inspect the main 8193771177 for landing gear leg repair instructions support within 50 and incorporate hours TISafter the these instructions. initial inspection Summarize and copy required by all correspondence paragraph (e)(1) of and send to FAA at this AD and the address thereafter at specified in intervals not to paragraph (f) of exceed 50 hours TIS. this AD. May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Standards Office, FAA. For information on any already approved alternative methods of compliance, contact
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Karl Schletzbaum, Aerospace Engineer, ACE112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri, 64106; telephone: (816) 3294146; facsimile: (816) 3294149.
Is There Other Information That Relates to This Subject?
(g) LBA Airworthiness Directive No. 2003272, dated October 7, 2003, and OMF Alert Service Bulletin 1107/0002, dated September 16, 2003, pertain to the subject of this AD.
Does This AD Incorporate Any Material by Reference?
(h) You must do the actions required by this AD following the instructions in OMF Aircraft Alert Service Bulletin 1107/0002, dated September 16, 2003. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Ostmecklenburgische Flugzeugbau GmbH, Flughafenstrasse, 17039 Trollenhagen, Federal Republic of Germany; telephone: 011 49 395 425600; facsimile: 011 49 395 42560 20. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 7416030. To view the AD docket,
go to the Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL 401, Washington, DC 20590001 or on the Internet at http://dms.dot.gov. The docket number is 2003CE67AD.

Issued in Kansas City, Missouri, on November 15, 2004. Scott L. Sedgwick,
Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 0425789 Filed 112404; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Karl Schletzbaum, Aerospace Engineer, ACE112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri, 64106; telephone: (816) 3294146; facsimile: (816) 3294149.