AD 2003-08-11

[Federal Register Volume 68, Number 78 (Wednesday, April 23, 2003)]
[Rules and Regulations]
[Pages 19937-19940]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 03-9691]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-15-AD; Amendment 39-13124; AD 2003-08-11]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, -200B, -200F, -
200C, -100B, -300, -100B SUD, -400, -400D, and -400F Series Airplanes; 
and Model 747SR 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 747-100, -200B, -200F, -200C, -100B, 
-300, -100B SUD, -400, -400D, and -400F series airplanes; and Model 
747SR

[[Page 19938]]

series airplanes. This action requires repetitive inspections to detect 
discrepancies of the actuator attach fittings of the inboard and 
outboard flaps, and follow-on and corrective actions as necessary. This 
action is necessary to detect and correct cracking and other damage of 
the actuator attach fittings of the trailing edge flaps, which could 
result in abnormal operation or retraction of a trailing edge flap, and 
possible loss of controllability of the airplane. This action is 
intended to address the identified unsafe condition.

DATES: Effective May 8, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 8, 2003.
    Comments for inclusion in the Rules Docket must be received on or 
before June 23, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-15-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#cbf2e6aaa5a6e6a2aab9a8a4a6a6aea5bf8badaaaae5aca4bd"><span class="__cf_email__" data-cfemail="5f66723e313272363e2d3c3032323a312b1f393e3e71383029">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2003-NM-15-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: Gary Oltman, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6443; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: The FAA has received reports of three 
fractures of the attach fittings of the trailing edge flap actuator on 
Boeing Model 747 series airplanes. The fractures have been attributed 
to corrosion and/or cracking. In one case, the fracture caused the flap 
to jam and resulted in an air turnback. In another case, the fractures 
occurred in the area of the upper journal. If not corrected, corroded 
or cracked attach fittings could fracture and result in abnormal 
operation or retraction of a trailing edge flap, and possible loss of 
controllability of the airplane.

Related Rulemaking

    On June 20, 2001, the FAA issued related AD 2001-13-12, amendment 
39-12292 (66 FR 34526, June 29, 2001), which applies to certain Boeing 
Model 747 series airplanes. That AD:
    [sbull] Requires repetitive inspections to detect cracks and 
corrosion around the lower bearing of the actuator attach fittings of 
the inboard and outboard flaps;
    [sbull] Requires repetitive overhauls for certain actuator attach 
fittings or repetitive replacement of the fittings with new fittings, 
as applicable, which terminates the repetitive inspections; and
    [sbull] Provides for replacement of actuator attach fittings with 
improved fittings, which terminates all requirements of the AD.
    The three incidents previously discussed occurred since AD 2001-13-
12 was issued. Those incidents occurred on airplanes that had been 
inspected in accordance with AD 2001-13-12. Consequently, the FAA has 
determined that the terminating action in AD 2001-13-12 (replacement 
with improved fittings) will not adequately address the unsafe 
condition. However, the service information cited in this new AD has 
been approved as an alternative method of compliance (AMOC) with the 
requirements of paragraphs (a) through (e) of AD 2001-13-12. The FAA 
may consider superseding that AD to incorporate the requirements of 
this AD as well as other requirements.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
747-57A2316, dated December 19, 2002, which describes procedures for, 
among other things, repetitive inspections of the attach fittings of 
the inboard and outboard flaps to detect discrepancies. The inboard 
fittings are to be inspected using borescopic and detailed visual 
methods; and the outboard fittings are to be inspected using 
borescopic, detailed visual, and ultrasonic methods. Discrepancies 
include surface corrosion, pitting, damaged cadmium plating, and 
cracking. Corrective/follow-on actions may include repetitive detailed 
visual inspections to detect bushing migration and cracking and other 
damage of the actuator attach fittings; repetitive application of 
corrosion-inhibiting compound; and replacement of the fittings with new 
or overhauled fittings, which terminates the repetitive inspections. 
The manufacturer advises that Boeing Service Bulletin 747-57A2316 
replaces Boeing Service Bulletin 747-57A2310, which was cited as the 
appropriate source of service information for the requirements of AD 
2001-13-12. Although Service Bulletin 747-57A2316 replaces Service 
Bulletin 747-57A2310, AD 2001-13-12 is still in effect. As stated 
previously, Service Bulletin 747-57A2316 has been approved as an AMOC 
for the requirements of paragraphs (a) through (e) of AD 2001-13-12.

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 detect and correct cracking and other damage of the 
actuator attach fittings of the trailing edge flaps, which could result 
in abnormal operation or retraction of a trailing edge flap, and 
possible loss of controllability of the airplane. This AD requires 
accomplishment of certain actions specified in Boeing Alert Service 
Bulletin 747-57A2316, described previously.

Interim Action

    This is considered to be interim action. Although Boeing Alert 
Service Bulletin 747-57A2316 specifies actions in addition to those 
required by this AD, only certain actions specified in the service 
bulletin are required by this AD. The FAA may consider issuing further 
rulemaking to require repetitive replacement of the fittings with new 
or overhauled fittings. However, because of the urgency of the 
identified unsafe condition, the FAA finds it necessary to issue this 
AD immediately without prior public comment. The planned compliance 
times for the additional actions would be long enough to practicably 
provide notice and opportunity for public comment.

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.

[[Page 19939]]

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.
    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 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 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 2003-NM-15-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

0
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

0
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]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2003-08-11 Boeing: Amendment 39-13124. Docket 2003-NM-15-AD.

    Applicability: All Model 747-100, -200B, -200F, -200C, -100B, -
300, -100B SUD, -400, -400D, and -400F series airplanes; and all 
Model 747SR 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 detect and correct cracking and other damage of the actuator 
attach fittings of the trailing edge flaps, which could result in 
abnormal operation or retraction of a trailing edge flap, and 
possible loss of controllability of the airplane, accomplish the 
following:

Inspection: Inboard Flap Attach Fittings

    (a) Perform borescopic and detailed inspections to detect 
discrepancies of the inboard flap attach fittings, in accordance 
with Part 1 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-57A2316, dated December 19, 2002. Discrepancies 
include corrosion, pitting, and damaged or missing cadmium plating. 
Do the inspection at the applicable time specified in paragraph 
(a)(1) or (a)(2) of this AD.

    Note 2: For the purposes of this AD, a detailed 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) If the age of the fittings can be determined: Inspect within 
14 years since the fittings were new or last overhauled, or within 
90 days after the effective date of this AD, whichever occurs later.
    (2) If the age of the fittings cannot be determined: Inspect 
within 90 days after the effective date of this AD.

    Note 3: The exceptions specified in flag note 4 of Figure 1 of 
Boeing Alert Service Bulletin 747-57A2316, dated December 19, 2002, 
apply to the requirements of paragraphs (a) and (b) of this AD.

Inspection: Outboard Flap Attach Fittings

    (b) Perform borescopic, detailed, and ultrasonic inspections to 
detect discrepancies of the outboard flap attach fittings, in 
accordance with Part 1 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2316, dated December 19, 2002. 
Discrepancies include surface corrosion, pitting, damaged or missing 
cadmium plating, and cracks. Do the inspection at the applicable 
time specified in paragraph (b)(1) or (b)(2) of this AD.
    (1) If the age of the fittings can be determined: Inspect within 
8 years since the fittings were new or last overhauled, or within 90 
days after the effective date of this AD, whichever occurs later.
    (2) If the age of the fittings cannot be determined: Inspect 
within 90 days after the effective date of this AD.

Follow-on Actions: No Discrepancies Found

    (c) If no discrepancy is found during any inspection required by 
paragraph (a) or (b) of this AD: Do the actions specified by either 
paragraph (c)(1) or paragraph (c)(2) of this AD.
    (1) Repeat the applicable inspections specified in paragraphs 
(a) and (b) of this AD at least every 9 months until the actions 
specified in paragraph (c)(2) of this AD have been accomplished.

[[Page 19940]]

    (2) Perform a detailed inspection of the fitting to detect 
cracks, corrosion, damaged cadmium plating, or bushing migration, in 
accordance with and at the time specified in Part 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2316, dated December 19, 2002. Do the follow-on actions in 
accordance with Parts 3, 4, and 5 of the Accomplishment Instructions 
of the service bulletin at the times specified in Figure 1 of the 
service bulletin, as applicable. Accomplishment of the actions 
specified by paragraph (c)(2) of this AD terminates the initial and 
repetitive inspection requirements of paragraphs (a), (b), and 
(c)(1) of this AD.

    Note 4: The exceptions specified in flag note 2 of Figure 1 of 
Boeing Alert Service Bulletin 747-57A2316, dated December 19, 2002, 
apply to those requirements of paragraphs (c)(2) and (d) of this AD 
that are specified in Part 2 of the service bulletin.

Corrective/Follow-on Actions: Discrepancies Found

    (d) If any discrepancy is found during any inspection required 
by paragraph (a), (b), or (c) of this AD: Perform applicable 
corrective and follow-on actions at the time specified and in 
accordance with Figure 1 of Boeing Alert Service Bulletin 747-
57A2316, dated December 19, 2002. Before further flight: Replace any 
discrepant fitting in accordance with Part 5 of the Accomplishment 
Instructions of the service bulletin, and accomplish the follow-on 
actions for the other fitting common to that flap in accordance with 
Part 2 of the Accomplishment Instructions of the service bulletin. 
Replacement of a fitting terminates the initial and repetitive 
inspections--specified in paragraphs (a), (b), and (c) of this AD--
for that fitting only.

Optional Action To Reset Compliance Schedule

    (e) Replacement of fittings with new or overhauled fittings, in 
accordance with Part 5 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2316, dated December 19, 2002, 
terminates the initial and repetitive inspection requirements of 
paragraphs (a), (b), and (c) of this AD.

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 Aircraft Certification 
Office (ACO), FAA. 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) The actions shall be done in accordance with Boeing Alert 
Service Bulletin 747-57A2316, dated December 19, 2002. 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 May 8, 2003.

    Issued in Renton, Washington, on April 14, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-9691 Filed 4-22-03; 8:45 am]
BILLING CODE 4910-13-P