AD 2000-13-51

[Federal Register Volume 65, Number 140 (Thursday, July 20, 2000)]
[Rules and Regulations]
[Pages 44977-44979]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-18280]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-216-AD; Amendment 39-11826; AD 2000-13-51]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 737-200 and -300 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting airworthiness directive (AD) 2000-13-51 that was sent 
previously to certain U.S. owners and operators of Boeing Model 737-200 
and -300 series airplanes by individual notices. This AD requires 
repetitive special detailed inspections to detect cracking of the main 
deck cargo door frames, their existing reinforcing angles (where 
applicable), and the attach holes of the latch fittings between frame 
station (FS) 361.87 and FS 498.12, and between water line (WL) 202.35 
and WL 213.00, in the area where the main deck cargo door latch 
fittings attach to the frames, and corrective actions, if necessary. 
This action is prompted by a report indicating that three of the 
subject airplanes had multiple cracks in the lower portion of the main 
deck cargo door frames and, in some cases, the reinforcing angles. The 
actions specified by this AD are intended to detect and correct 
cracking of the lower portion of the main deck cargo door frames, which 
could result in sudden depressurization, loss or opening of the main 
deck cargo door during flight, and loss of control of the airplane.

DATES: Effective July 25, 2000, to all persons except those persons to 
whom it was made immediately effective by emergency AD 2000-13-51, 
issued July 3, 2000, which contained the requirements of this 
amendment.
    Comments for inclusion in the Rules Docket must be received on or 
before September 18, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-216-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
<a href="/cdn-cgi/l/email-protection#ccf5e1ada2a1e1a5adbeafa3a1a1a9a2b88caaadade2aba3ba"><span class="__cf_email__" data-cfemail="70495d111e1d5d191102131f1d1d151e04301611115e171f06">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-216-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    Information pertaining to this amendment may be examined at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Small Airplane Directorate, Atlanta Aircraft 
Certification Office, One Crown Center, 1895 Phoenix Boulevard, Suite 
450, Atlanta, Georgia; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Rany Azzi, Aerospace Engineer, 
Airframe and Propulsion Branch, ACE-117A, FAA, Atlanta Aircraft 
Certification Office, One Crown Center, 1895 Phoenix Boulevard, Suite 
450, Atlanta, Georgia 30337-2748, telephone (770) 703-6083; fax (770) 
703-6097.

SUPPLEMENTARY INFORMATION: On July 3, 2000, the FAA issued emergency AD 
2000-13-51, which is applicable to all Boeing Model 737-200 and -300 
series airplanes equipped with a main deck cargo door installed in 
accordance with Supplemental Type Certificate (STC) SA2969SO.
    That action was prompted by a report indicating that three of the 
subject airplanes had multiple cracks in the lower portion of the main 
deck cargo door frames and, in some cases, the reinforcing angles. The 
exact cause of the cracking is unknown at this time. The area of the 
cracking is between frame station (FS) 361.87 and FS 498.12 where the 
latch fittings attach to the main deck cargo door frames. Such cracking 
in the lower portion of the main deck cargo door frames could cause 
reduced structural integrity of the main deck cargo door. This 
condition, if not corrected, could result in sudden depressurization, 
loss or opening of the main deck cargo door during flight, and loss of 
control of the airplane.

[[Page 44978]]

Explanation of Requirements of the Rule

    Since the unsafe condition described is likely to exist or develop 
on other airplanes of the same type design, the FAA issued emergency AD 
2000-13-51 to detect and correct cracking of the lower portion of the 
main deck cargo door frames, which could result in sudden 
depressurization, loss or opening of the main deck cargo door during 
flight, and loss of control of the airplane. The AD requires repetitive 
special detailed inspections to detect cracking of the main deck cargo 
door frames, their existing reinforcing angles (where applicable), and 
the attach holes of the latch fittings between FS 361.87 and FS 498.12, 
and between WL 202.35 and WL 213.00, in the area where the main deck 
cargo door latch fittings attach to the frames, and corrective actions, 
if necessary.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual notices 
issued on July 3, 2000 to all known U.S. owners and operators of Boeing 
Model 737-200 and -300 series airplanes equipped with a main deck cargo 
door installed in accordance with STC SA2969SO. These conditions still 
exist, and the AD is hereby published in the Federal Register as an 
amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 
39.13) to make it effective to all persons.

Reporting Requirements

    This AD also requires that operators report the results of the 
special detailed inspection to the FAA. Because the cause of the 
addressed cracking is not currently known, the intent of these required 
inspection reports is to enable the FAA to determine how widespread 
such cracking problems may be in the affected fleet.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications shall identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-216-AD.'' The postcard will be date stamped 
and returned to the commenter.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket.
    A copy of it, if filed, may be obtained from the Rules Docket at 
the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

    Accordingly, pursuant to 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 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. Section 39.13 is amended by adding the following new 
airworthiness directive:

2000-13-51  Boeing: Amendment 39-11826. Docket 2000-NM-216-AD.

    Applicability: Model 737-200 and -300 series airplanes equipped 
with a main deck cargo door installed in accordance with 
Supplemental Type Certificate (STC) SA2969SO; certificated in any 
category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (c) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct cracking of the lower portion of the main 
deck cargo door frames, which could result in sudden 
depressurization, loss or opening of the main deck cargo door during 
flight, and loss of control of the airplane, accomplish the 
following:
    (a) Prior to further flight after the effective date of this AD, 
perform a special detailed inspection using a borescope to detect 
cracking of the main deck cargo door frames, their existing 
reinforcing angles (where applicable), and the attach holes of the 
latch fittings between frame station (FS) 361.87 and FS 498.12, and 
between water line (WL) 202.35 and WL 213.00, in the area where the 
main deck cargo door latch fittings attach to the frames.
    (1) If no cracking is detected, repeat the inspection thereafter 
at intervals not to exceed 150 flight cycles.
    (2) If any cracking is detected, prior to further flight, 
accomplish the requirements of

[[Page 44979]]

either paragraph (a)(2)(i) or (a)(2)(ii) of this AD.
    (i) Replace all discrepant parts with new parts having the same 
part numbers and repeat the special detailed inspection using a 
borescope thereafter at intervals not to exceed 150 flight cycles.
    (ii) Repair in accordance with a method approved by the Manager, 
Atlanta Aircraft Certification Office (ACO), FAA.

    Note 2: For the purpose of this AD a special detailed inspection 
is defined as: ``An intensive examination of a specific item(s), 
installation, or assembly to detect damage, failure, or 
irregularity. The examination is likely to make extensive use of 
specialized inspection techniques and or equipment. Intricate 
cleaning and substantial access or disassembly procedure may be 
required.''

Reporting Requirements

    (b) Within 10 days after accomplishing the actions required by 
paragraph (a) of this AD, submit a report of any findings of 
cracking to the Manager, FAA, Atlanta ACO, One Crown Center, 1895 
Phoenix Boulevard, suite 450, Atlanta, Georgia, fax (770) 703-6097. 
Information collection requirements contained in this regulation 
have been approved by the Office of Management and Budget (OMB) 
under the provisions of the Paperwork Reduction Act of 1980 (44 
U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-
0056.

Alternative Methods of Compliance

    (c) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Atlanta ACO. Operators shall submit 
their requests through an appropriate FAA Principal Maintenance 
Inspector, who may add comments and then send it to the Manager, 
Atlanta ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Atlanta ACO.

Special Flight Permits

    (d) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a location where the 
requirements of this AD can be accomplished.

Effective Date

    (e) This amendment becomes effective on July 25, 2000, to all 
persons except those persons to whom it was made immediately 
effective by emergency AD 2000-13-51, issued on July 3, 2000, which 
contained the requirements of this amendment.

    Issued in Renton, Washington, on July 13, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-18280 Filed 7-19-00; 8:45 am]
BILLING CODE 4910-13-U