

[Federal Register: September 19, 2007 (Volume 72, Number 181)]
[Proposed Rules]               
[Page 53495-53498]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr19se07-24]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-29226; Directorate Identifier 2006-NM-256-AD]
RIN 2120-AA64

 
Airworthiness Directives; McDonnell Douglas Model DC-9-81 (MD-81) 
and DC-9-82 (MD-82) Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain McDonnell Douglas Model DC-9-81 (MD-81) and DC-9-82 (MD-82) 
airplanes. This proposed AD would require, for certain airplanes, 
inspecting for cracking of the fuselage skin at the upper corners of 
the forward passenger doorjamb, installing or replacing doublers as 
applicable, and doing applicable repairs. This proposed AD results from 
reports of fatigue cracking in the fuselage skin at the upper corners 
of the forward passenger doorjamb. We are proposing this AD to prevent 
cracking of the fuselage skin at the upper corners of the forward 
passenger doorjamb, which could lead to loss of overall structural 
integrity of the airplane.

DATES: We must receive comments on this proposed AD by November 5, 
2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 

the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov
 and follow the instructions for sending your 

comments electronically.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room

[[Page 53496]]

W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room W12-140 on the ground floor of the 
West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, 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 proposed AD.

FOR FURTHER INFORMATION CONTACT: Roger Durbin, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5233; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2007-
29226; Directorate Identifier 2006-NM-256-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will 

also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.


Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Operations office between 9 

a.m. and 5 p.m., Monday through Friday, except Federal holidays. The 
Docket Operations office (telephone (800) 647-5527) is located on the 
ground level of the West Building at the DOT street address stated in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after the Docket Management System receives them.

Discussion

    We have received a report that fatigue cracking has been discovered 
in the fuselage skin at the upper corners of the forward passenger 
doorjamb on certain Model DC-9/MD-80 airplanes. This condition, if not 
corrected, could lead to loss of overall structural integrity of the 
airplane.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin MD80-53A298, dated 
August 1, 2006. The alert service bulletin describes procedures for a 
low-frequency eddy current (LFEC) or a high-frequency eddy current 
(HFEC) inspection, depending on airplane configuration, for cracking of 
the fuselage skin at the upper corners of the forward passenger 
doorjamb; and applicable corrective actions. The compliance time for 
the initial inspection is before accumulating 37,500 total flight 
cycles, or within 3,575 flight cycles (whichever is later).
    The corrective actions include:
     For Group 1, Configuration 1, airplanes on which no 
cracking is found: Either repeating the LFEC inspection at intervals of 
3,575 flight cycles; or installing external aluminum doublers within 
3,575 flight cycles after the last inspection, and doing an HFEC 
inspection within 28,000 flight cycles after doing the installation, 
and repetitively at 20,000-flight-cycle intervals.
     For Group 1, Configuration 1, airplanes on which any crack 
is found that is 2.0 inches or shorter in length: Repair before further 
flight, and do an HFEC inspection within 28,000 flight cycles after the 
repair, and repetitively at 20,000-flight-cycle intervals.
     For Group 1, Configuration 1, airplanes on which any crack 
is found that is longer than 2.0 inches; for Group 1, Configurations 2 
and 3, airplanes on which any crack is found beyond the edge of the 
doublers; and for Group 1, Configuration 4, airplanes: Contact Boeing 
for repair instructions before further flight.
     For Group 1, Configuration 2, airplanes on which no crack 
is found beyond the edge of the steel doublers: Replace existing steel 
doublers with aluminum doublers, and repair upper corners within 6,000 
flight cycles after the initial inspection; and do an HFEC inspection 
within 28,000 flight cycles after the repair, and repetitively at 
20,000-flight-cycle intervals.
     For Group 1, Configuration 3, airplanes on which no cracks 
are found beyond the edge of the aluminum doublers: Repeat the HFEC 
inspection at 20,000-flight-cycle intervals.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between Proposed AD and Alert Service Bulletin.''

Differences Between Proposed AD and Alert Service Bulletin

    For all airplanes, the alert service bulletin specifies to contact 
the manufacturer for instructions on how to repair certain conditions, 
but this proposed AD would require repairing those conditions in one of 
the following ways:
     Using a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by an Authorized Representative 
for the Boeing Commercial Airplanes Delegation Option Authorization 
Organization whom we have authorized to make those findings.
    For airplane configuration 4: Where the alert service bulletin 
specifies to contact the manufacturer for repair instructions before 
further flight, to avoid unnecessarily grounding airplanes, this 
proposed AD would require performing repairs within 90 days after the 
effective date of this proposed AD.

Costs of Compliance

    There are about 76 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 46 airplanes of 
U.S. registry. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD, at an average labor 
rate of $80 per work hour. The proposed actions vary depending upon the 
airplane configuration.

[[Page 53497]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
              Action                Work hours          Parts           Cost per airplane        Fleet cost
----------------------------------------------------------------------------------------------------------------
LFEC inspection..................            1  None needed.........  $80, per inspection   Up to $3,680, per
                                                                       cycle.                inspection cycle.
HFEC inspection..................            1  None needed.........  $80, per inspection   Up to $3,680, per
                                                                       cycle.                inspection cycle.
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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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    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 regulatory evaluation of the estimated costs to 
comply with this proposed 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.

The Proposed Amendment

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

PART 39--AIRWORTHINESS 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. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

McDonnell Douglas: Docket No. FAA-2007-29226; Directorate Identifier 
2006-NM-256-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by November 
5, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to McDonnell Douglas Model DC-9-81 (MD-81) 
and DC-9-82 (MD-82) airplanes; certificated in any category; as 
identified in Boeing Alert Service Bulletin MD80-53A298, dated 
August 1, 2006.

Unsafe Condition

    (d) This AD results from a report of fatigue cracking in the 
fuselage skin at the upper corners of the forward passenger 
doorjamb. We are issuing this AD to prevent cracking of the fuselage 
skin at the upper corners of the forward passenger doorjamb, which 
could lead to loss of overall 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.

Repetitive Inspections and Corrective Actions for Configuration 1, 2, 
and 3 Airplanes

    (f) For airplanes identified as Configuration 1, 2, or 3 in 
Boeing Alert Service Bulletin MD80-53A298, dated August 1, 2006: At 
the applicable times specified in paragraph 1.E., ``Compliance,'' of 
the alert service bulletin, do a low-frequency eddy current (LFEC) 
or high-frequency eddy current (HFEC) inspection, as applicable, for 
cracking of the fuselage skin at the upper corners of the forward 
passenger doorjamb; and do all applicable corrective actions 
(repetitive inspections, installation of doublers, replacements, and 
repairs), except as provided by paragraph (g) of this AD. Do the 
actions in accordance with the Accomplishment Instructions of the 
alert service bulletin. Where the alert service bulletin specifies a 
compliance time after the date on the service bulletin, this AD 
requires compliance within the specified compliance time after the 
effective date of this AD.

Repair of Certain Conditions

    (g) If any crack is found during any inspection required by 
paragraph (f) of this AD and Boeing Alert Service Bulletin MD80-
53A298, dated August 1, 2006, specifies to contact Boeing for repair 
instructions: Before further flight, repair using a method approved 
in accordance with the procedures specified in paragraph (i) of this 
AD.

Corrective Action for Configuration 4 Airplanes

    (h) For airplanes identified as Configuration 4 in Boeing Alert 
Service Bulletin MD80-53A298, dated August 1, 2006: Within 90 days 
after the effective date of this AD, repair using a method approved 
in accordance with the procedures specified in paragraph (i) of this 
AD.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested in accordance with the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by 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 14 CFR 25.571, Amendment 45, and the 
approval must specifically refer to this AD.


[[Page 53498]]


    Issued in Renton, Washington, on September 10, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-18447 Filed 9-18-07; 8:45 am]

BILLING CODE 4910-13-P
