[Federal Register Volume 68, Number 213 (Tuesday, November 4, 2003)]
[Proposed Rules]
[Pages 62408-62409]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-27671]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-273-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727 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 all Boeing Model 727 airplanes. 
This proposal would require an inspection of the bolts used to attach 
the forward cone bolt to the engine flange to determine if the 
attachment bolts are either H-11 steel bolts or cadmium-plated bolts. 
This proposal would also require replacement of either H-11 steel bolts 
or cadmium-plated bolts with new corrosion-resistant steel bolts. This 
action is necessary to prevent undetected cracking of the H-11 bolts or 
excessive wear of the cadmium-plated bolts, which would compromise the 
primary load path of the engine support and could result in separation 
of the engine from the airplane. This action is intended to address the 
identified unsafe condition.

DATES: Comments must be received by December 19, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-273-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. 2002-NM-273-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.
    The service information referenced in the proposed rule may be 
obtained from Boeing Commercial Airplane Group, 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: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437; 
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:
    [sbull] 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.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] 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 2002-NM-273-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. 2002-NM-273-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports indicating that H-11 steel bolts used 
to attach the forward cone bolt to the engine flange of Boeing Model 
727 airplanes are susceptible to stress corrosion cracking, although no 
reports of related cracking have been received. Also, the cadmium-
plated bolts that were also used in production are not sufficiently 
wear-resistant for the application. This condition, if not corrected, 
could compromise the primary load path of the engine support, which 
could result in separation of the engine from the airplane.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
727-71A0402, dated January 18, 2001, which describes procedures for 
inspecting the

[[Page 62409]]

bolts that are used to attach the forward cone bolt to the engine 
flange to determine if H-11 steel bolts or cadmium-plated bolts are 
installed. The service bulletin also describes procedures for replacing 
H-11 steel bolts or cadmium-plated bolts with corrosion-resistant steel 
bolts. 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 service bulletin described previously, except as discussed below.

Differences Between Proposed Rule and Service Bulletin

    Operators should note that, although Boeing Alert Service Bulletin 
727-71A040s, dated January 18, 2001, recommends that the affected bolts 
be inspected and replaced at the next convenient scheduled maintenance 
period not to exceed 3,000 flight cycles, this proposal would require 
that the affected bolts be inspected and replaced within 18 months or 
3,000 flight cycles from the effective date of this AD, whichever is 
earlier.

Cost Impact

    There are approximately 1,148 Model 727 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 715 
airplanes of U.S. registry would be affected by this proposed AD, that 
it would take approximately 3 work hours 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 $139,425, or $195 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 2002-NM-273-AD.

    Applicability: All Model 727, 727C, 727-100, 727-100C, 727-200, 
and 727-200F series airplanes, certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent undetected cracking of the H-11 steel bolts or 
cadmium-plated bolts, which would compromise the primary load path 
of the engine support and could result in separation of the engine 
from the airplane, accomplish the following:

Inspection and Replacement

    (a) Within 18 months or 3,000 flight cycles from the effective 
date of this AD, whichever is earlier, inspect the bolts that are 
used to attach the forward cone bolt to the engine flange to 
determine if they are H-11 steel bolts (part number (P/N ) 
BACB30GU12-64), cadmium-plated bolts (P/N BACB30LM12-64), or 
corrosion-resistant bolts (P/N NAS6712E64), per the Accomplishment 
Instructions of Boeing Alert Service Bulletin 727-71A0402, dated 
January 18, 2001.
    (1) If corrosion-resistant bolts (P/N NAS6712E64) are installed, 
no further action is required by this paragraph.
    (2) If any H-11 steel bolt or cadmium-plated bolt is found, 
before further flight, replace the bolt with a new corrosion-
resistant bolt (P/N NAS6712E64), according to the Accomplishment 
Instructions in the service bulletin.

Parts Installation

    (b) As of the effective date of this AD, no person may install 
an H-11 steel bolt (P/N BACB30GU12-64) or a cadmium-plated bolt (P/N 
BACB30LM12-64) to attach the forward cone bolt to the engine flange 
on any airplane.

Alternative Methods of Compliance

    (c) In accordance with 14 CFR 39.19, the Manager, Seattle 
Aircraft Certification Office, FAA, is authorized to approve 
alternative methods of compliance for this AD.

    Issued in Renton, Washington, on October 29, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-27671 Filed 11-3-03; 8:45 am]
BILLING CODE 4910-13-P