AD 2001-22-12

[Federal Register Volume 66, Number 211 (Wednesday, October 31, 2001)]
[Rules and Regulations]
[Pages 54920-54923]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-27214]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-281-AD; Amendment 39-12491; AD 2001-22-12]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to all Boeing Model 727 series airplanes. This action 
requires repetitive inspections for migration or corrosion of the outer 
hinge pins that attach the horizontal stabilizer to the vertical fin, 
and various follow-on actions, if necessary. This action also provides 
other repetitive inspections for cracking or corrosion of the hinge 
pins, which terminate the required repetitive inspections for migration 
or corrosion; these inspections are optional for airplanes on which no 
migration or corrosion is found. This action is necessary to find and 
fix corrosion or cracking in the hinge pins of the horizontal 
stabilizer, which could lead to structural degradation of the hinge of

[[Page 54921]]

the horizontal stabilizer and result in loss of the horizontal 
stabilizer and consequent loss of controllability of the airplane. This 
action is intended to address the identified unsafe condition.

DATES: Effective November 15, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 15, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before December 31, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-281-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#f5ccd8949b98d89c9487969a9898909b81b5939494db929a83"><span class="__cf_email__" data-cfemail="f9c0d4989794d490988b9a9694949c978db99f9898d79e968f">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-281-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 this AD 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; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Walter Sippel, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2774; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: The FAA has received reports of cracks and 
corrosion in the outer hinge pins that attach the horizontal stabilizer 
to the vertical fin on several Boeing Model 727 series airplanes. The 
cracks in the outer hinge pins, which are made of 4330 steel, have been 
attributed to stress corrosion. These cracks often initiate in corroded 
areas of the hinge pin not protected by chrome plating. Corrosion has 
also been found on inner fail-safe hinge pins. Corrosion or cracking in 
the outer hinge pins of the horizontal stabilizer could lead to 
structural degradation of the stabilizer hinge joint and consequent 
loss of the horizontal stabilizer, which would result in loss of 
controllability of the airplane.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
727-55A0090, Revision 1, dated September 20, 2001, which describes 
procedures for repetitive detailed visual inspections for migration or 
corrosion of the outer hinge pins of the horizontal stabilizer, and 
various follow-on actions, if necessary. The follow-on actions include:
    <bullet> A torque test (referred to in the service bulletin as a 
``torque check'') of the nut on the outer hinge pins, and reduction of 
the torque values for the nut on the outer hinge pins, if necessary.
    <bullet> Repetitive detailed visual and magnetic particle 
inspections for corrosion or cracking of the outer and inner hinge pins 
(which also involves removal of outer and inner hinge pins, as 
necessary, and application of corrosion preventative compound or grease 
on the hinge pins).
    <bullet> Replacement of migrated, cracked, or broken hinge pins 
with new or serviceable hinge pins.
    Accomplishment of the repetitive detailed visual and magnetic 
particle inspections for corrosion or cracking of the outer and inner 
hinge pins, as necessary, including all associated actions, eliminates 
the need for the repetitive detailed visual inspections for migration 
or corrosion of the hinge pins.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design, this AD is 
being issued to find and fix corrosion or cracking in the outer hinge 
pins of the horizontal stabilizer, which could lead to structural 
degradation of the hinge of the horizontal stabilizer and result in 
loss of the horizontal stabilizer and consequent loss of 
controllability of the airplane. This AD requires accomplishment of the 
actions specified in the service bulletin described previously, except 
as discussed below.

Differences Between This AD and Service Bulletin

    This AD differs from the referenced service bulletin in the 
following ways:
    <bullet> The service bulletin specifies that the manufacturer may 
be contacted for disposition of repair conditions. However, this AD 
requires the repair of those conditions to be accomplished per a method 
approved by the FAA, or per data meeting the type certification basis 
of the airplane approved by a Boeing Company Designated Engineering 
Representative who has been authorized by the Manager, Seattle Aircraft 
Certification Office, to make such findings.
    <bullet> The referenced service bulletin recommends accomplishment 
of the repetitive detailed visual and magnetic particle inspections for 
corrosion or cracking of the outer and inner hinge pins; and provides 
initial and repetitive compliance times for these inspections. However, 
for airplanes on which no migrated, cracked, broken, or corroded hinge 
pins are found, this AD provides for accomplishment of the repetitive 
detailed visual and magnetic particle inspections as an option which 
terminates the requirement for repetitive inspections for pin migration 
or corrosion.

Interim Action

    This is considered to be interim action. The FAA is currently 
considering requiring, for all airplanes, accomplishment of the 
inspections in Part 3 and Part 4 of the service bulletin, which--as 
described above--are specified in this AD as optional for airplanes on 
which no migrated, cracked, broken, or corroded hinge pins are found. 
However, the planned compliance time for such inspections is 
sufficiently long so that notice and opportunity for prior public 
comment will be practicable.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

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

[[Page 54922]]

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.
    Submit comments using the following format:
    <bullet> 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.
    <bullet> For each issue, state what specific change to the AD is 
being requested.
    <bullet> 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 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 2001-NM-281-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, Incorporation by 
reference, 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:

2001-22-12  Boeing: Amendment 39-12491. Docket 2001-NM-281-AD.

    Applicability: All Model 727 series airplanes, certificated in 
any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 (f) 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 find and fix corrosion or cracking in the hinge pins of the 
horizontal stabilizer, which could lead to structural degradation of 
the hinge of the horizontal stabilizer and result in loss of the 
horizontal stabilizer and consequent loss of controllability of the 
airplane, accomplish the following:

One-Time Inspection and Torque Test, and Follow-On Actions (Certain 
Airplanes)

    (a) For outer hinge pins that attach the horizontal stabilizer 
to the vertical fin on which the actions in Boeing Service Bulletin 
727-55-0086, Revision 1, dated June 23, 1988, have NOT been 
accomplished prior to the effective date of this AD: Within 90 days 
after the effective date of this AD, do a one-time detailed visual 
inspection for migration or corrosion of the outer hinge pins, per 
Part 1 of the Work Instructions of Boeing Alert Service Bulletin 
727-55A0090, Revision 1, dated September 20, 2001. If no migration 
or corrosion of an outer hinge pin is found, before further flight, 
do a torque test (referred to in the service bulletin as a ``torque 
check'') of the nuts on the outer hinge pins to determine the 
existing torque values and if any hinge pins are cracked or broken, 
per Boeing Alert Service Bulletin 727-55A0090, Revision 1.

    Note 2: Boeing Service Bulletin 727-55-0086, Revision 1, dated 
June 23, 1988, recommends a one-time inspection and application of 
primer to prevent corrosion on the outer hinge pins of the 
horizontal stabilizer on all Boeing Model 727 series airplanes. That 
service bulletin also specifies a reduction of torque values for 
installing the nuts of the outer hinge pins, which is intended to 
prevent stress corrosion cracking.


    Note 3: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

    (1) For any outer hinge pin that is not migrated, cracked, 
broken, or corroded, torque the nut on the outer hinge pin within 
the limits specified in Boeing Alert Service Bulletin 727-55A0090, 
Revision 1, per that service bulletin, and within 180 days after 
accomplishment of paragraph (a) of this AD, do the initial 
inspection in paragraph (b) of this AD, and applicable follow-on 
actions.
    (2) For any migrated, cracked, or broken outer hinge pin that is 
not corroded: Do paragraph (c) of this AD.
    (3) For any corroded outer hinge pin: Do paragraph (d) of this 
AD.

Repetitive Inspections

    (b) For outer hinge pins of the outer horizontal stabilizer on 
which the actions in Boeing Service Bulletin 727-55-0086, Revision 
1, dated June 23, 1988, HAVE been accomplished prior to the 
effective date of this AD, and airplanes identified in paragraph 
(a)(1) of this AD: Within 90 days after the effective date of this 
AD, except as provided by paragraph (a) of this AD, do a detailed 
visual inspection for migration or corrosion of both the outer and 
inner hinge pins, per Part 2 of the Work Instructions of Boeing 
Alert Service Bulletin 727-55A0090, Revision 1, dated September 20, 
2001. If no migration or corrosion of a hinge pin is found, repeat 
the inspection every 180 days, per Boeing Alert Service Bulletin 
727-55A0090, Revision 1, until paragraph (e) of this AD is 
accomplished.

Follow-On Corrective Actions: Migrated, Cracked, or Broken Hinge Pin

    (c) If any migration of the hinge pin or a cracked or broken 
hinge pin is found during an inspection per paragraph (a) or (b) of 
this AD, but NO corrosion is found: Before further flight, do all 
actions in Part 4 of the Work Instructions of Boeing Alert Service 
Bulletin 727-55A0090, Revision 1, dated September 20, 2001, per 
paragraph (e) of this AD.


[[Page 54923]]


    Note 4: Parts 1 and 2 of the Work Instructions of Boeing Alert 
Service Bulletin 727-55A0090, Revision 1, refer to Figures 4 and 5 
of that service bulletin as follow-on corrective actions for certain 
conditions. Figures 4 and 5 of that service bulletin specify 
accomplishment of Parts 3 and 4, respectively, of the Work 
Instructions of that service bulletin.

Follow-On Corrective Actions: Corrosion

    (d) If any corrosion of a hinge pin is found during an 
inspection per paragraph (a) or (b) of this AD: Do paragraph (d)(1) 
or (d)(2) of this AD, as applicable.
    (1) If corrosion is found on the inner hinge pin only: Before 
further flight, do all actions in Part 3 of the Work Instructions of 
Boeing Alert Service Bulletin 727-55A0090, Revision 1, dated 
September 20, 2001, per paragraph (e) of this AD.
    (2) If corrosion is found on the outer hinge pin: Before further 
flight, do all actions in Part 4 of the Work Instructions of Boeing 
Alert Service Bulletin 727-55A0090, Revision 1, dated September 20, 
2001, per paragraph (e) of this AD.

Optional Inspections

    (e) Accomplishment of detailed visual and magnetic particle 
inspections for corrosion or cracking including all associated 
actions (such as removal of outer, inner, or outer AND inner hinge 
pins, as applicable, and application of corrosion preventative 
compound or grease), per Part 3 or 4, as applicable, of the Work 
Instructions of Boeing Alert Service Bulletin 727-55A0090, Revision 
1, dated September 20, 2001; AND accomplishment of applicable 
follow-on actions per paragraphs (e)(1) and (e)(2) of this AD, as 
applicable; terminates the repetitive inspections required by 
paragraph (b) of this AD.
    (1) If any corrosion or cracking is found, replace the outer, 
inner, or outer AND inner hinge pins, as applicable, with new or 
serviceable pins, per Boeing Alert Service Bulletin 727-55A0090, 
Revision 1, EXCEPT, where the service bulletin specifies to contact 
Boeing for appropriate action, before further flight, repair per a 
method approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA; or per data meeting the type certification basis 
of the airplane approved by a Boeing Company Designated Engineering 
Representative who has been authorized by the Manager, Seattle ACO, 
to make such findings. For a repair method to be approved by the 
Manager, Seattle ACO, as required by this paragraph, the Manager's 
approval letter must specifically reference this AD. And,
    (2) Repeat the inspections in Part 3 or 4 of the service 
bulletin, as applicable, at the applicable time specified in the 
``REPEAT INSPECTIONS'' column of the table under paragraph 1.E. 
``Compliance'' of Boeing Alert Service Bulletin 727-55A0090, 
Revision 1.

Alternative Methods of Compliance

    (f) 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, Seattle ACO. Operators shall submit 
their requests through an appropriate FAA Principal Maintenance 
Inspector, who may add comments and then send it to the Manager, 
Seattle ACO.

    Note 5: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (g) Special flight permits may be issued in accordance with 
sections 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.

Incorporation by Reference

    (h) Except as provided by paragraph (e)(1) of this AD, the 
actions shall be done in accordance with Boeing Alert Service 
Bulletin 727-55A0090, Revision 1, dated September 20, 2001. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Boeing Commercial Airplane Group, 
P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (i) This amendment becomes effective on November 15, 2001.

    Issued in Renton, Washington, on October 24, 2001.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-27214 Filed 10-30-01; 8:45 am]
BILLING CODE 4910-13-U