FR Doc 05-167

[Federal Register: January 5, 2005 (Volume 70, Number 3)]
[Proposed Rules]
[Page 729-731]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05ja05-27]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19988; Directorate Identifier 2004-NM-30-AD]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 727-200 Series Airplanes
Equipped With a No. 3 Cargo Door

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing Model 727-200 series airplanes equipped with a No. 3
cargo door. This proposed AD would require repetitive detailed and high
frequency eddy current inspections for cracking of the forward, lower
corner frame and forward end of the lower beam of the No. 3 cargo door,
and corrective actions if necessary. The proposed AD provides an
optional terminating action for the repetitive inspections. This
proposed AD is prompted by reports of cracking at the forward, lower
corner frame and lower beam of the No. 3 cargo door. We are proposing
this AD to detect and correct cracking of the forward, lower corner
frame and forward end of the lower beam of the No. 3 cargo door, which
could result in failure of the affected door stops, loss of the cargo
door, and consequent rapid decompression of the airplane.

DATES: We must receive comments on this proposed AD by February 22,
2005.

ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow

the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your

comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
By fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
You can get the service information identified in this proposed AD
from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington
98124-2207.
You may examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or in person at the Docket Management Facility,

U.S. Department of Transportation, 400 Seventh Street SW., room PL-401,
on the plaza level of the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT:
Technical information: 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.
Plain language information: Marcia Walters, marcia.walters@faa.gov.

SUPPLEMENTARY INFORMATION:

Docket Management System (DMS)

The FAA has implemented new procedures for maintaining AD dockets
electronically. As of May 17, 2004, new AD actions are posted on DMS
and assigned a docket number. We track each action and assign a
corresponding directorate identifier. The DMS AD docket number is in
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier
(``Old Docket Number'') as a cross-reference for searching purposes.

Comments Invited

We invite you to submit any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2004-19988;
Directorate Identifier 2004-NM-30-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments submitted by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will

also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit http://dms.dot.gov.

We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications that affect you. You can get more information about
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.Examining
the Docket

You may examine the AD docket in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the DOT

[[Page 730]]

street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the DMS receives them.

Discussion

We have received reports of cracking on the forward, lower corner
frame and lower beam of the No. 3 cargo door, on certain Boeing Model
727-200 series airplanes. The affected airplanes had approximately
32,773 to 70,187 flight hours and 33,383 to 54,541 pressurization
cycles. Investigation revealed that the cracking was caused by fatigue
as a result of the cabin pressurization cycles. This condition, if not
corrected, could result in failure of the affected door stops, loss of
the cargo door, and consequent rapid decompression of the airplane.

Relevant Service Information

We have reviewed Boeing Special Attention Service Bulletin 727-52-
0149, dated October 16, 2003. The service bulletin describes procedures
for repetitive detailed and high frequency eddy current (HFEC)
inspections for cracking of the forward, lower corner frame and forward
end of the lower beam of the No. 3 cargo door. Generally, the initial
inspection is done before accumulating 30,000 total flight cycles or
within 2,000 flight cycles after the release date of the service
bulletin, whichever is later. The service bulletin also states the
inspections should be repeated at intervals not to exceed 4,500 flight
cycles. The service bulletin also includes procedures for corrective
actions. For airplanes on which cracking is found, the corrective
actions include repairing areas with cracking. The repair procedures
include fabricating/installing repair parts and a preventative
modification, which eliminates the need for the repetitive inspections.
The preventative modification includes installing beam modification
parts and a frame reinforcement angle on the No. 3 cargo door. The
preventative modification can also be done on airplanes on which no
cracking is found. We have determined that accomplishing the actions
specified in the service bulletin will adequately address the unsafe
condition.

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. Therefore, we are proposing this AD, which
would require repetitive detailed and HFEC inspections for cracking of
the forward, lower corner frame and lower beam of the No. 3 cargo door,
and corrective actions if necessary. The proposed AD would require you
to use the service information described previously to perform these
actions. The proposed AD provides an optional terminating action for
the repetitive inspections.

Costs of Compliance

This proposed AD would affect about 390 Model 727-200 series
airplanes worldwide. The following table provides the estimated costs
for U.S. operators to comply with this proposed AD.

Estimated Costs
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Average Number of
Work labor Cost per U.S.- Fleet
Action hours rate per Parts airplane registered cost
hour airplanes
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Detailed and HFEC Inspections, per inspection 2 $65 None $130 274 $35,620
cycle.......................................
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Authority for this Rulemaking

The FAA's authority to issue rules regarding aviation safety is
found in Title 49 of the United States Code. Subtitle I, Section 106
describes the authority of the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more detail the scope of the agency's
authority.
This rulemaking is promulgated under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this AD.

Regulatory Findings

We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify that the 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. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):

Boeing: Docket No. FAA-2004-19988; Directorate Identifier 2004-NM-
30-AD.

Comments Due Date

(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by February 22, 2005.

Affected ADs

(b) None.

Applicability

[[Page 731]]

cargo door, as listed in Boeing Special Attention Service Bulletin
727-52-0149, dated October 16, 2003; certificated in any category.

Unsafe Condition

(d) This AD was prompted by reports of cracking at the forward,
lower corner frame and lower beam of the No. 3 cargo door. We are
proposing this AD to detect and correct cracking of the forward,
lower corner frame and forward end of the lower beam of the No. 3
cargo door, which could result in failure of the affected door
stops, loss of the cargo door, and consequent rapid decompression of
the airplane.

Compliance

(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.

Repetitive Detailed and High Frequency Eddy Current (HFEC) Inspections

(f) Do detailed and HFEC inspections for cracking of the
forward, lower corner frame and forward end of the lower beam of the
No. 3 cargo door by accomplishing all of the applicable actions
specified in the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 727-52-0149, dated October 16, 2003. Do
the inspections at the times specified in the applicable table in
paragraph 1.E., ``Compliance,'' of the service bulletin, except as
required by paragraph (g) of this AD. Repeat the inspections
thereafter at intervals not to exceed 4,500 flight cycles. Doing the
applicable actions in paragraph (h) or (j) of this AD terminates the
repetitive inspections.
(g) Where the service bulletin specified in paragraph (f) of
this AD provides a threshold relative to the release date of the
service bulletin, this AD requires compliance within the applicable
threshold following the effective date of this AD, if the ``total
airplane flight cycles'' or ``total replaced door flight cycles''
threshold has been exceeded.

Corrective Actions

(h) For airplanes on which cracking is found during any
inspection required by paragraph (f) of this AD: Before further
flight, do all of the applicable corrective actions specified in the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 727-52-0149, dated October 16, 2003. Repairing any affected
area terminates the repetitive inspections required by paragraph (f)
of this AD.

Parts Installation

(i) Any replacement No. 3 cargo door installed on any airplane
after the effective date of this AD must be inspected or modified in
accordance with either paragraph (i)(1) or (i)(2) of this AD, as
applicable.
(1) If the number of total flight cycles on the door can be
positively determined: Do the actions required by paragraphs (f) and
(h) of this AD, as applicable, or paragraph (j) of this AD. Do the
actions at the times specified in Table 2 of paragraph 1.E.,
``Compliance,'' of Boeing Special Attention Service Bulletin 727-52-
0149, dated October 16, 2003.
(2) If the number of total flight cycles on the door cannot be
positively determined: Do the actions required by paragraphs (f) and
(h) of this AD, as applicable, or paragraph (j) of this AD, before
installing the door.

Optional Terminating Action

(j) Concurrently with doing the inspection required by paragraph
(f) of this AD, if no cracking is found, doing the preventative
modification specified in paragraph 3.B.2. of the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 727-52-
0149, dated October 16, 2003, terminates the repetitive inspections
required by paragraph (f) of this AD.

Alternative Methods of Compliance (AMOCs)

(k)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
(2) An AMOC that provides an acceptable level of safety may be
used for any repair for cracking required by this AD, if it is
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, the approval must
specifically reference this AD.

Issued in Renton, Washington, on December 27, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-167 Filed 1-4-05; 8:45 am]

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