Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F Airplanes, 14393-14394 [E7-5554]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 72, Number 59 (Wednesday, March 28, 2007)]
[Rules and Regulations]
[Pages 14393-14394]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-5554]



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Federal Register / Vol. 72, No. 59 / Wednesday, March 28, 2007 / 
Rules and Regulations

[[Page 14393]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25850; Directorate Identifier 2006-NM-128-AD; 
Amendment 39-15004; AD 2007-07-04]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
McDonnell Douglas Model MD-11 and -11F airplanes. This AD requires 
revising the maintenance inspection program that provides for 
inspection of principal structural elements (PSEs) and replacement of 
safe-life parts, to incorporate a new revision to the MD-11 
Airworthiness Limitations Instructions. The revision reduces inspection 
intervals for fatigue cracking of certain PSEs, and expands the 
inspection area for a certain other PSE. This AD results from a revised 
damage tolerance analysis. We are issuing this AD to detect and correct 
fatigue cracking of certain PSEs, which could adversely affect the 
structural integrity of the airplane.

DATES: This AD becomes effective May 2, 2007.

ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Boeing Commercial Aircraft Group, Long Beach Division, 3855 
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and 
Service Management, Dept. C1-L5A (D800-0024), for the service 
information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Maureen Moreland, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5238; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: 

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at https://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to all McDonnell Douglas 
Model MD-11 and -11F airplanes. That NPRM was published in the Federal 
Register on September 20, 2006 (71 FR 54941). That NPRM proposed to 
require revising the maintenance inspection program that provides for 
inspection of principal structural elements (PSEs) and replacement of 
safe-life parts, to incorporate a new revision to the MD-11 
Airworthiness Limitations Instructions (ALI). The revision would reduce 
inspection intervals for fatigue cracking of certain PSEs, and expand 
the inspection area for a certain other PSE.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received.

Request To Extend Certain Initial Inspection Thresholds

    Boeing has requested that we provide an extension of the initial 
inspection threshold for certain airplanes. Boeing states that the ALI 
specified in the NPRM would require reducing the initial inspection 
threshold for PSE 54.52.01.1 from 19,000 total flight cycles to 10,200 
total flight cycles. Boeing adds that for PSEs 54.21.01.1 (54.52.01.1), 
57.21.02.1, and 57.23.01.1, a minimum of 24 months is required to 
accomplish the initial inspection after paragraph (f) of the NPRM is 
done; the initial inspection times for these PSEs were reduced. Boeing 
also states that, as of July 2006, there are approximately 50 airplanes 
exceeding 10,000 total flight cycles. Boeing points out that the ALI 
would reduce the initial inspection threshold for PSEs 57.21.02.1 and 
57.23.01.1 from 19,900 total flight cycles to 15,750 and 15,250 total 
flight cycles respectively. Boeing notes that, as of July 2006, there 
are six airplanes with more than 12,000 total flight cycles. 
Additionally, Boeing points out that the ALI would reduce the 
repetitive inspection interval for PSE 57.21.05.1 from 10,000 flight 
cycles to 3,200 flight cycles. Approximately 50 airplanes would have 
already accomplished the inspection, but would be planning for a 
10,000-flight-cycle repetitive interval instead of a 3,200-flight-cycle 
repetitive interval. Boeing asserts that a substantial increase in the 
compliance time requirements for those PSE inspections is necessary to 
prevent an immediate hardship on the operators of these airplanes.
    For the reasons cited by Boeing, we agree with its request to 
extend certain inspection compliance times. We have determined that PSE 
number 54.21.01.1, as cited in Boeing's comment, is a typographical 
error and we have used the correct PSE number, 54.52.01.1, in this AD. 
We have added a new paragraph (h) to this AD to specify those certain 
PSE inspection compliance times, and re-identified the remaining 
paragraphs accordingly.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD with the change described previously. 
These changes will neither increase the economic burden on any operator 
nor increase the scope of the AD.

Costs of Compliance

    There are about 102 airplanes of the affected design in the 
worldwide fleet. This AD affects about 93 airplanes of

[[Page 14394]]

U.S. registry. The maintenance and inspection program revision takes 
about 1 work hour per airplane, at an average labor rate of $80 per 
work hour. Based on these figures, the estimated cost of the AD for 
U.S. operators is $7,440, or $80 per airplane, per inspection cycle.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    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.
    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 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 regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2007-07-04 McDonnell Douglas: Amendment 39-15004. Docket No. FAA-
2006-25850; Directorate Identifier 2006-NM-128-AD.

Effective Date

    (a) This AD becomes effective May 2, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all McDonnell Douglas Model MD-11 and -
11F airplanes, certificated in any category.

    Note 1: This AD requires revisions to certain operator 
maintenance documents to incorporate new inspections for fatigue 
cracking of principal structural elements (PSEs). Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to incorporate the inspections described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according 
to paragraph (i) of this AD. The request should include a 
description of changes to the required inspections that will ensure 
the continued damage tolerance of the affected structure. The FAA 
has provided guidance for this determination in Advisory Circular 
(AC) 25-1529-1.

Unsafe Condition

    (d) This AD results from a revised damage tolerance analysis. We 
are issuing this AD to detect and correct fatigue cracking of 
certain principal structural elements (PSEs), which could adversely 
affect the structural integrity of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Revision of Airworthiness Limitations Section

    (f) Except as provided by paragraph (h) of this AD: Within 18 
months after the effective date of this AD, revise the Airworthiness 
Limitations section of the Instructions for Continued Airworthiness, 
Airworthiness Limitations Instructions (ALI), according to a method 
approved by the Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA. Boeing MD-11 ALI, Report Number MDC-K5225, Revision 11, 
dated March 2006, is one approved method.
    (g) Except as provided by paragraph (i) of this AD: After the 
actions specified in paragraph (f) of this AD have been done, no 
alternative inspection intervals or replacement times may be 
approved for the PSEs and safe-life limited parts specified in 
Boeing MD-11 ALI Report Number MDC-K5225, Revision 11, dated March 
2006.

Compliance Times for Inspections

    (h) Accomplish the initial threshold and repetitive inspection 
intervals specified in the ALI, as applicable, at the times 
specified in paragraphs (h)(1) and (h)(2) of this AD.
    (1) For PSEs 54.52.01.1, 57.21.02.1, and 57.23.01.1: Accomplish 
the initial inspection within 24 months after accomplishment of the 
requirements in paragraph (f) of this AD, or within the initial 
inspection interval specified in the ALI, whichever occurs later.
    (2) For airplanes on which the initial inspection of PSE 
57.21.05.1 has been accomplished as of the effective date of this 
AD: Repeat the inspection within 24 months after accomplishment of 
the requirements in paragraph (f) of this AD, or within 3,200 flight 
cycles after accomplishment of the initial inspection, whichever 
occurs later. Repeat the inspection thereafter at intervals not to 
exceed 3,200 flight cycles.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Los Angeles ACO, has the authority to 
approve AMOCs for this AD, if requested in accordance with the 
procedures found in 14 CFR 39.19.
    (2) An AMOC that provides an acceptable level of safety may be 
used for any repair required by accomplishing the actions of this 
AD, if it is approved by an Authorized Representative for the Boeing 
Commercial Airplanes Delegation Option Authorization Organization 
who has been authorized by the Manager, Los Angeles ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (3) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Material Incorporated by Reference

    (j) None.

    Issued in Renton, Washington, on March 19, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-5554 Filed 3-27-07; 8:45 am]
BILLING CODE 4910-13-P