[Federal Register Volume 69, Number 115 (Wednesday, June 16, 2004)]
[Proposed Rules]
[Pages 33587-33590]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-13501]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-131-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727, 727C, 727-100, -100C, 
and -200 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Boeing Model 727, 727C, 
727-100, -100C, and -200 series airplanes. This proposal would require 
an inspection of the forward trunnion attach fittings of the main 
landing gear (MLG), inspections of the attach fitting holes of the 
forward trunnion attach fittings if necessary, replacement of the 
forward trunnion attach fittings if necessary, and corrective actions 
if necessary. This action is necessary to detect and correct cracks and 
corrosion on the attach fitting holes of the forward trunnion attach 
fittings of the MLG, which could result in the collapse of the MLG. 
This action is intended to address the identified unsafe condition.

DATES: Comments must be received by August 2, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-131-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: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2003-NM-131-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 or 2000 or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6456; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the proposed 
AD is being requested.

[[Page 33588]]

     Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2003-NM-131-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2003-NM-131-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports of cracks and corrosion in the attach 
bolt holes of the forward trunnion attach fittings of the main landing 
gear (MLG) on certain Boeing Model 727 series airplanes. Forward 
trunnion attach fittings made of 7079-T6 aluminum are prone to stress 
corrosion cracking even if they have been shot peened. This condition, 
if not detected and corrected, could result in the collapse of the MLG.

Other Related Rulemaking

    On October 2, 2001, the FAA issued AD 2001-20-09, amendment 39-
12457 (66 FR 51843, October 11, 2001), applicable to all Boeing Model 
727 series airplanes, which currently requires repetitive inspections 
of the bearing support fitting of the forward trunnion on the MLG to 
detect corrosion and cracking; follow-on actions, if necessary; and 
repair/rework of the support fitting, or replacement with a new or 
repaired/reworked fitting. That AD is to be done in accordance with 
Boeing Alert Service Bulletin 727-57A0179, Revision 3, dated September 
2, 1999; Boeing Alert Service Bulletin 727-57A0179, Revision 4, dated 
July 13, 2000; or Boeing Service Bulletin 727-57A0179, Revision 5, 
dated December 20, 2000. The actions specified by that AD are intended 
to prevent failure of the support fitting, which could result in 
collapse of the MLG during normal operations; consequent damage to the 
airplane structure; and injury to flight crew, passengers, or ground 
personnel.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
727-57A0132, Revision 3, dated March 20, 2003, which describes 
procedures for an inspection of the forward trunnion attach fittings of 
the MLG to determine the part number; detailed and high frequency eddy 
current inspections of the attach fitting holes of the forward trunnion 
attach fittings having part number 65-19296-1 through -8 (made of 7079-
T6 aluminum) for cracks and corrosion if necessary; and corrective 
actions if necessary. The corrective actions include reworking the 
attach fitting holes, repairing the attach fitting holes, and replacing 
the forward trunnion attach fitting with a new forward trunnion attach 
fitting. Replacement of the 7079-T6 attach fittings with a 7075-T73511 
or 7050-T7451 attach fitting is considered terminating action for the 
service bulletin.
    Accomplishment of the actions specified in the service bulletin is 
intended to adequately address the identified unsafe condition.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require accomplishment of the actions specified in 
the Boeing Alert Service Bulletin 727-57A0132, Revision 3, dated March 
20, 2003, described previously, except as discussed below.

Differences Between Proposed Rule and Service Bulletin

    The compliance time in section 1.E. of the Boeing Alert Service 
Bulletin 727-57A0132, Revision 3, dated March 20, 2003, specifies to do 
the actions ``For airplanes over 20 years old (since the original 
airplane delivery date) that have a 7079-T6 MLG forward trunnion attach 
fitting'' at the later time of ``two years after the release of 
Revision 3 the service bulletin'' or ``ten years after the last 
inspection/rework of the attach fitting per a prior release of this 
service bulletin.'' However, for these same airplanes, paragraph (b) of 
this proposed AD specifies to do the actions at the latest of the 
following times:
    1. Prior to airplanes reaching 240 months old since the date of 
issuance of the original Airworthiness Certificate or the date of 
issuance of the original Export Certificate of Airworthiness; or
    2. Within 18 months after the effective date of this AD; or
    3. Within 120 months after the last inspection/rework/repair of the 
attach fitting per Boeing Service Bulletin 727-57A0132, dated June 28, 
1974; Revision 1, dated October 31, 1975; or Revision 2, dated April 
24, 1981; or Boeing Alert Service Bulletin 727-57A0132, Revision 3, 
dated March 20, 2003.
    We have determined that ``For airplanes over 20 years old'' may be 
interpreted as the AD applies only to airplanes with the stated age as 
of the effective date of the AD. We have determined that the age of the 
airplanes is intended to be the initial threshold. Thus, ``prior to 
airplanes reaching 240 months old'' will include all affected 
airplanes. We have also determined that ``original airplane delivery 
date'' may be interpreted differently by different operators. We find 
that ``date of issuance of the original Airworthiness Certificate or 
the date of issuance of the Export Certificate of Airworthiness, 
whichever occurs first'' is generally understood within the industry 
and records will always exist that establish these dates with 
certainty. We also did not include the qualifying phrase ``that have a 
7079-T6 MLG forward trunnion attach fitting'' because the first action 
in the proposed AD is to determine which airplanes have a 7079-T6 
forward trunnion attach fitting of the MLG.
    Although the service bulletin recommends one option for the 
compliance time as ``two years after the release of Revision 3 the 
service bulletin,'' we have determined that the two year interval would 
not address the identified unsafe condition soon enough to ensure an 
adequate level of safety for the affected fleet. In developing this 
option for the compliance time for this AD, we coordinated with the 
manufacturer and considered the degree of urgency associated with the 
subject unsafe condition, the average utilization of the affected 
fleet, and the time necessary to perform the inspection (1 hour). In 
light of all of these factors, we find that the compliance time of 
``within 18 months after the effective date of this AD'' represents an 
appropriate interval of time for affected airplanes to continue to 
operate without compromising safety.
    Although paragraph 7 of ``Part II'' of the Accomplishment 
Instructions of the service bulletin only lists part number P/N 65-
19296U13 (LH) or P/N 65-19296U14 (RH) as acceptable new attach 
fittings, paragraphs (d)(2) and (e) of the proposed AD lists the 
following acceptable new attach fittings: P/N65-19296-9, -10, -13, or -
14; P/N 65-

[[Page 33589]]

99909-1724 or -1727; P/N 65-19296U13 or P/N 65-19296U14.
    Although the service bulletin specifies concurrent accomplishment 
of Boeing Alert Service Bulletin 727-57A0179, Revision 3 or later, this 
AD does not require concurrent accomplishment of service bulletin 727-
57A0179, Revision 3 or later. AD 2001-20-09 already requires 
accomplishment of the actions in Boeing Alert Service Bulletin 727-
57A0179, Revision 3, dated September 2, 1999; Revision 4, dated July 
13, 2000; or Boeing Service Bulletin 727-57A0179, Revision 5, dated 
December 20, 2000.

Cost Impact

    There are approximately 523 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 309 airplanes of U.S. registry 
would be affected by this proposed AD, that it would take approximately 
1 work hour per airplane to accomplish the proposed inspection, and 
that the average labor rate is $65 per work hour. Based on these 
figures, the cost impact of the proposed AD on U.S. operators is 
estimated to be $20,085, or $65 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the proposed requirements of 
this AD action, and that no operator would accomplish those actions in 
the future if this proposed AD were not adopted. The cost impact 
figures discussed in AD rulemaking actions represent only the time 
necessary to perform the specific actions actually required by the AD. 
These figures typically do not include incidental costs, such as the 
time required to gain access and close up, planning time, or time 
necessitated by other administrative actions.

Regulatory Impact

    The regulations proposed herein 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. Therefore, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this 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) if promulgated, 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. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting 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.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

Boeing: Docket 2003-NM-131-AD.

    Applicability: Boeing Model 727, 727C, 727-100, -100C, and -200 
series airplanes, line numbers 1 through 887 inclusive; certificated 
in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct cracks and corrosion on the attach fitting 
holes of the forward trunnion attach fittings of the main landing 
gear (MLG), which could result in the collapse of the MLG, 
accomplish the following:

Service Bulletin References

    (a) The term ``service bulletin,'' as used in this AD, means 
Boeing Alert Service Bulletin 727-57A0132, Revision 3, dated March 
20, 2003.

Initial Inspection

    (b) Perform an inspection of the forward trunnion attach 
fittings of the MLG to determine the part number (P/N) of the attach 
fitting, in accordance with ``Part 1'' of the Accomplishment 
Instructions of the service bulletin, at the latest of the times 
specified in paragraphs (b)(1), (b)(2), and (b)(3) of this AD:
    (1) Prior to airplanes reaching 240 months old since the date of 
issuance of the original Airworthiness Certificate or the date of 
issuance of the original Export Certificate of Airworthiness; or
    (2) Within 18 months after the effective date of this AD; or
    (3) Within 120 months after the last inspection/rework/repair of 
the attach fitting per Boeing Service Bulletin 727-57A0132, dated 
June 28, 1974; Revision 1, dated October 31, 1975; or Revision 2, 
dated April 24, 1981; or Boeing Alert Service Bulletin 727-57A0132, 
Revision 3, dated March 20, 2003.

Corrective Actions

    (c) If, during the inspection required by paragraph (b) of this 
AD, both attach fittings are found to have P/N 65-19296-9, -10, -13, 
or -14; P/N 65-99909-1724 or -1727; P/N 65-19296U13 or P/N 65-
19296U14 (attach fitting made of 7075-T73511 or 7050-T7451 
aluminum); no further action is required by this paragraph.
    (d) If, during the inspection required by paragraph (b) of this 
AD, any attach fitting is found to have P/N 65-19296-1 through -8 
inclusive (attach fitting made of 7079-T6 aluminum): Before further 
flight, perform the actions in paragraphs (d)(1) and (d)(2) of this 
AD, as applicable.
    (1) Do detailed and high frequency eddy current inspections of 
the attach fitting holes for cracks and corrosion, repair any crack 
or corrosion found, and rework the attach fitting holes in 
accordance with Figures 4 and 5 of the service bulletin, except as 
provided by paragraph (d)(2) of this AD.
    (2) If the attach fitting hole cannot be reworked or repaired in 
accordance with Figures 4 and 5 of the service bulletin: Before 
further flight, replace the attach fitting with a new attach fitting 
that has P/N 65-19296-9, -10, -13, or -14, P/N 65-99909-1724 or -
1727, P/N 65-19296U13, or P/N 65-19296U14, in accordance with 
paragraph 7 of ``Part II'' of the Accomplishment Instructions of the 
service bulletin. Accomplishment of this replacement is terminating 
action for that fitting.

Terminating Action

    (e) Within 120 months after the effective date of this AD, 
replace attach fittings that have P/N 65-19296-1 through -8 (attach 
fittings made of 7079-T6 aluminum) with new attach fittings that 
have P/N 65-19296-9, -10, -13, or -14, P/N 65-99909-1724 or -1727, 
P/N 65-19296U13, or P/N 65-19296U14 (attach fittings made of 7075-
T73511 or 7050-T7451 aluminum), in accordance with paragraph 7 of 
``Part II'' of the Accomplishment Instructions of the service 
bulletin. Replacement of all attach fittings made of 7079-T6 
aluminum with new attach fittings made of 7075-T73511 or 7050-T7451 
aluminum terminates the requirements of paragraph (d) of this AD.

Parts Installation

    (f) As of the effective date of this AD, no person shall 
install, on any airplane, an attach fitting, P/N 65-19296-1, -2, -3, 
-4, -5, -6, -7, or -8 (attach fitting made of 7079-T6 aluminum), 
unless it has been inspected/reworked/repaired in accordance with 
paragraph (d) of this AD.

Alternative Methods of Compliance

    (g)(1) In accordance with 14 CFR 39.19, the Manager, Seattle 
Aircraft Certification Office, FAA, is authorized to approve 
alternative methods of compliance (AMOCs) for this AD.
    (2) An AMOC that provides an acceptable level of safety may be 
used for any rework/repair required by this AD, if it is approved by 
a Boeing Company Designated Engineering Representative (DER) who has

[[Page 33590]]

been authorized by the Manager, Seattle ACO, to make such findings. 
For a rework/repair method to be approved, the approval must 
specifically reference this AD.

    Issued in Renton, Washington, on June 7, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-13501 Filed 6-15-04; 8:45 am]
BILLING CODE 4910-13-P