[Federal Register Volume 68, Number 84 (Thursday, May 1, 2003)]
[Proposed Rules]
[Pages 23231-23235]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-10728]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-66-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to all Boeing Model 727 series 
airplanes, that currently requires repetitive pre-modification 
inspections to detect cracks in the forward support fitting of the 
number 1 and number 3 engines; and repair, if necessary. That AD also 
provides for an optional high frequency eddy current inspection, and, 
if possible, modification of the fastener holes; and various follow-on 
actions; which would terminate the repetitive pre-modification 
inspections. This action would expand the area to be inspected; require 
accomplishment of the previously optional (and subsequently revised) 
modification, which would terminate certain repetitive inspections; and 
add repetitive post-modification inspections to detect cracking of the 
fastener holes, and corrective actions if necessary. The actions 
specified by the proposed AD are intended to prevent fatigue cracking 
of the forward support fitting of the number 1 and number 3 engines, 
which could result in failure of the support fitting and consequent 
separation of the engine from the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Comments must be received by June 16, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-66-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-66-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

[[Page 23232]]

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-66-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-66-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On February 21, 1997, the FAA issued AD 97-05-08, amendment 39-9952 
(62 FR 9359, March 3, 1997), applicable to all Boeing Model 727 series 
airplanes, to require repetitive pre-modification inspections to detect 
cracks in the forward support fitting of the number 1 and number 3 
engines; and repair, if necessary. That AD also provides for an 
optional high frequency eddy current inspection, and, if possible, 
modification of the fastener holes; and various follow-on actions. 
Accomplishment of those optional actions would terminate the repetitive 
pre-modification inspections. That action was prompted by reports 
indicating that fatigue cracks were found in the forward support 
fitting of the number 1 and number 3 engines. The requirements of that 
AD are intended to detect and correct such fatigue cracking, which 
could result in failure of the support fitting and consequent 
separation of the engine from the airplane.

Actions Since Issuance of Previous AD

    Since that AD was issued, the FAA has received reports of 
additional cracking found on the forward support fitting of the number 
1 and number 3 engines on Boeing Model 727 series airplanes. Those 
cracks were found at new locations (not identified in AD 97-05-08) on 
airplanes that had accumulated between 18,200 and 44,200 total flight 
cycles. The cracking has been attributed to fatigue due to corrosion-
pitting damage on the surface of fastener holes in the support 
fittings.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Service Bulletin 727-
54A0010, Revision 6, dated August 23, 2001, including an Evaluation 
Form. Revision 4 of the service bulletin was cited as the appropriate 
source of service information for accomplishment of the actions 
required by AD 97-05-08. Revision 5 was issued to divide the airplane 
effectivity into two groups, add more locations to be inspected, add 
inspections until the terminating action is accomplished, revise the 
instructions for the modification, and add post-modification repetitive 
inspections. Revision 6 was issued to change part numbers for certain 
fasteners and revise the repetitive intervals for inspection of the 
upper outboard flange. Accomplishment of the actions specified in 
Revision 6 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 supersede AD 97-05-08 to continue to require 
repetitive inspections to detect cracking in the forward support 
fitting of the number 1 and number 3 engines. This proposed AD also 
would expand the area to be inspected; require accomplishment of the 
previously optional (and subsequently revised) modification, which 
would terminate certain repetitive inspections; and add repetitive 
post-modification inspections to detect cracking of the fastener holes, 
and corrective action if necessary. The actions would be required to be 
accomplished in accordance with Revision 6 of the service bulletin 
described previously.

Differences Between Proposed AD and Service Information

    Although the service bulletin specifies that Boeing may be 
contacted for disposition of certain repair conditions, this proposal 
would require the repair of those conditions to be accomplished in 
accordance with a method approved by the FAA, or in accordance with 
data meeting the type certification basis of the airplane approved by a 
Boeing Company Designated Engineering Representative who has been 
authorized by the FAA to make such findings.
    Although the service bulletin recommends that operators submit a 
completed Evaluation Form and a report of damage that exceeds certain 
limits, this proposed AD would not require such reports.

Explanation of Proposed Change to Existing Requirements

    The FAA has changed all references to a ``detailed visual 
inspection'' in the existing AD to ``detailed inspection'' in this 
proposed AD. Note 2 has been added to this proposed AD to define this 
type of inspection.

Cost Impact

    There are approximately 1,382 airplanes of the affected design in 
the worldwide fleet. The FAA estimates that 915 airplanes of U.S. 
registry would be affected by this proposed AD.
    The FAA provides the following cost estimates for this proposed AD:

----------------------------------------------------------------------------------------------------------------
                                                   Average                               Number of
              Action                 Work hours     hourly     Parts cost    Cost per       U.S.      U.S. fleet
                                                  labor rate                 airplane    airplanes       cost
----------------------------------------------------------------------------------------------------------------
AD 97-05-08 inspections, per                  2          $60           $0         $120          915        None.
 inspection cycle.................
Inspections before structural                14           60            0          840          915      768,600
 rework, per inspection cycle.....
Structural rework.................            7           60        7,875        8,295          915    7,589,925
Inspections after structural                 12           60            0          720          915      658,800
 rework, per inspection cycle.....
----------------------------------------------------------------------------------------------------------------

    The cost impact figures discussed above are 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,

[[Page 23233]]

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 removing amendment 39-9952 (62 FR 
9359, March 3, 1997), and by adding a new airworthiness directive (AD), 
to read as follows:

Boeing: Docket 2002-NM-66-AD. Supersedes AD 97-05-08, Amendment 39-
9952.
    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 (s)(1) 
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 prevent fatigue cracking of the forward support fitting of 
the number 1 and number 3 engines, which could result in failure of 
the support fitting and consequent separation of the engine from the 
airplane, accomplish the following:

Restatement of Requirements of AD 97-05-08

Inspections

    (a) Within 100 days or 600 flight cycles after March 18, 1997 
(the effective date of AD 97-05-08, amendment 39-9952), whichever 
occurs first, accomplish paragraphs (a)(1), (a)(2), and (a)(3) of 
this AD, in accordance with Boeing Service Bulletin 727-54A0010, 
Revision 4, dated January 30, 1997.
    (1) Perform a visual inspection to detect cracks of the upper 
and lower flanges, and the vertical web of the forward support 
fitting of the number 1 and number 3 engines, in accordance with 
Part 1--Pre-Modification Inspections of the Accomplishment 
Instructions of the service bulletin.
    (2) Perform a high frequency eddy current (HFEC) inspection to 
detect cracks of the forward flange of the support fitting adjacent 
to the collars of two fasteners of the number 1 and number 3 
engines, in accordance with Part 1--Pre-Modification Inspections of 
the Accomplishment Instructions of the service bulletin.
    (3) Perform a detailed inspection to detect cracks of the upper 
and lower flanges adjacent to six fasteners of the fitting of the 
number 1 and number 3 engines, in accordance with Part 1--Pre-
Modification Inspections of the Accomplishment Instructions of the 
service bulletin.

    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.''

    (b) If no crack is detected during the inspections required by 
paragraph (a) of this AD, repeat those inspections thereafter at 
intervals not to exceed 100 days or 600 flight cycles, whichever 
occurs first, until the initial inspections required by paragraph 
(d) of this AD have been accomplished.
    (c) If any crack is detected during any inspection required by 
paragraph (a) of this AD, prior to further flight, repair the 
forward support fitting in accordance with a method approved by the 
Manager, Seattle Aircraft Certification Office (ACO), FAA.

New Requirements of This AD

    Note 3: Where there are differences between the service bulletin 
and this AD, this AD prevails.

Inspections: All Airplanes

    (d) For all airplanes: Within 600 flight cycles or 100 days 
after the effective date of this AD, whichever occurs first, inspect 
the forward support fitting of the number 1 and number 3 engines, as 
specified in paragraphs (d)(1), (d)(2), (d)(3), (d)(4), and (d)(5) 
of this AD, in accordance with Part I of the Accomplishment 
Instructions of Boeing Service Bulletin 727-54A0010, Revision 6, 
dated August 23, 2001. Accomplishment of these initial inspections 
terminates the inspection requirements of paragraphs (a) and (b) of 
this AD.
    (1) Perform a general visual inspection to detect corrosion and 
cracking of the fittings in areas inboard of the side of the body, 
in accordance with Figure 1 of the service bulletin. If any 
corrosion is found, before further flight, remove the corrosion in 
accordance with Figure 5 of the service bulletin, and then perform a 
general visual inspection to detect cracking of the area, in 
accordance with the service bulletin.

    Note 4: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

    (2) Perform a HFEC inspection to detect cracking of the upper 
and lower horizontal flanges and post tangs of the fittings from 
inside the airplane, in accordance with Figure 1 of the service 
bulletin.
    (3) Perform a general visual inspection to detect cracking and 
corrosion of the fittings in areas outboard of the side of the body, 
in accordance with Figure 1 of the service bulletin. If any 
corrosion is found, before further flight, remove the corrosion in 
accordance with Figure 5 of the service bulletin, and perform a 
general visual inspection to detect cracking of the area, in 
accordance with the service bulletin.
    (4) Perform a detailed inspection to detect cracking and 
corrosion of the web in areas outboard of the side of the body, in 
accordance with Figure 1 of the service bulletin. If any corrosion 
is found, before further flight, remove the corrosion in accordance 
with Figure 5 of the service bulletin, and perform thickness 
measurements and detailed and HFEC inspections of the vertical web 
inboard and outboard of the side of the body to detect corrosion and 
cracking, in accordance with Figure 2 of the service bulletin.
    (5) Perform detailed and HFEC inspections to detect cracking of 
the upper and lower

[[Page 23234]]

horizontal flanges at the side of the body, in accordance with 
Figure 1 of the service bulletin.

Additional Inspections: Group 2 Airplanes

    (e) For Group 2 airplanes, as identified in Boeing Service 
Bulletin 727-54A0010, Revision 6, dated August 23, 2001: Within 600 
flight cycles or 100 days after the effective date of this AD, 
whichever occurs first, inspect the forward support fitting of the 
number 1 and number 3 engines at the firewall to detect cracking, as 
specified in paragraphs (e)(1), (e)(2), (e)(3), and (e)(4) of this 
AD, in accordance with Part I of the Accomplishment Instructions of 
the service bulletin.
    (1) Perform a detailed inspection to detect cracking of the aft 
side of the upper horizontal flange, in accordance with Figure 1 of 
the service bulletin.
    (2) Perform a low frequency eddy current (LFEC) or an open hole 
HFEC inspection to detect cracking of the aft side of the upper 
horizontal flange, in accordance with Figure 1 of the service 
bulletin.
    (3) Perform a detailed inspection to detect cracking of the aft 
side of the lower horizontal flange, in accordance with Figure 1 of 
the service bulletin.
    (4) Perform a HFEC inspection to detect cracking of the aft side 
of the lower horizontal flange, in accordance with Figure 1 of the 
service bulletin.

No Cracking Found: Follow-on Inspections, All Airplanes

    (f) For all airplanes: If no cracking is found during any 
inspection required by paragraph (d) of this AD, repeat the 
applicable inspections within the applicable intervals specified in 
paragraph 1.E., Table 1, of Boeing Service Bulletin 727-54A0010, 
Revision 6, dated August 23, 2001.

No Cracking Found: Additional Follow-on Inspections, Group 2 
Airplanes

    (g) For Group 2 airplanes only: If no cracking is found during 
the inspections required by paragraph (e) of this AD, repeat the 
inspections on the upper and lower outboard flange at the firewall 
within the applicable intervals specified in paragraph 1.E., Table 
1, of Boeing Service Bulletin 727-54A0010, Revision 6, dated August 
23, 2001.
    (1) Repeat the inspections of the UPPER outboard flange at the 
firewall until the modification required by paragraph (j) of this AD 
has been done.
    (2) Repeat the inspections of the LOWER outboard flange at the 
firewall indefinitely. There is no terminating action for the 
inspections of this area.

    Note 5: Boeing Service Bulletin 727-54A0010, Revision 6, dated 
August 23, 2001, does not provide instructions for modifying the 
fastener holes of the lower outboard flange at the firewall.

Cracking Found: Any Airplane

    (h) For any airplane: If any crack is found during any 
inspection required by paragraph (d), (e), (f), or (g) of this AD, 
before further flight, do the actions specified in either paragraph 
(h)(1) or (h)(2) of this AD.
    (1) Replace or repair the fitting in accordance with a method 
approved by the Manager, Seattle ACO; or per data meeting the type 
certification basis of the airplane approved by a Boeing Company 
Designated Engineering Representative (DER) who has been authorized 
by the Manager, Seattle ACO, to make such findings. For a repair 
method to be approved, the approval must refer specifically to this 
AD; or
    (2) Do the modification specified in paragraph (j) of this AD.

Web Thickness Less Than 0.130 Inch: Any Airplane

    (i) For any airplane: If the web thickness measured during 
accomplishment of paragraph (d)(4) of this AD is less than 0.130 
inch, before further flight, replace or repair the fitting in 
accordance with a method approved by the Manager, Seattle ACO; or 
per data meeting the type certification basis of the airplane 
approved by a Boeing Company DER who has been authorized by the 
Manager, Seattle ACO, to make such findings. For a repair method to 
be approved, the approval must refer specifically to this AD.

Modification

    (j) Except as required by paragraphs (h), (i), and (q) of this 
AD: Within 3,000 flight cycles or 24 months after the effective date 
of this AD, whichever occurs first, modify the fastener holes, in 
accordance with Part II of the Accomplishment Instructions of Boeing 
Service Bulletin 727-54A0010, Revision 6, dated August 23, 2001. 
Accomplishment of the modification terminates the repetitive 
inspections required by paragraphs (f) and (g)(1) of this AD.

Modification per Prior Service Bulletin Version

    (k) For airplanes modified before the effective date of this AD 
in accordance with Boeing Service Bulletin 727-54A0010, Revision 4, 
dated January 30, 1997: Paragraph (j) of this AD requires 
accomplishment of additional procedures in accordance with Revision 
6 of the service bulletin. To the extent that certain modification 
procedures were performed in accordance with Revision 4, those 
actions do not need to be repeated when performing the modification 
required in paragraph (j) above.
    (l) A modification done before the effective date of this AD in 
accordance with Boeing Alert Service Bulletin 727-54A0010, Revision 
5, dated February 15, 2001, is acceptable for compliance with the 
requirements of paragraph (j) of this AD.

Post-Modification Inspections

    (m) Inspect as specified in paragraphs (m)(1), (m)(2), and (n) 
of this AD, as applicable, to detect cracking and corrosion, in 
accordance with Part III of the Accomplishment Instructions of 
Boeing Service Bulletin 727-54A0010, Revision 6, dated August 23, 
2001. Inspections done before the effective date of this AD in 
accordance with Boeing Alert Service Bulletin 727-54A0010, Revision 
5, dated February 15, 2001, are acceptable for compliance with the 
corresponding inspection requirements of this paragraph.
    (1) For all airplanes: Do an open hole HFEC inspection of the 
fastener holes in the forward support fitting of the number 1 and 
number 3 engines, at the locations shown in Figure 4 of the service 
bulletin.
    (2) For Group 2 airplanes: Do an open hole HFEC inspection of 
the fastener holes in the forward support fitting of the number 1 
and number 3 engines, at the locations shown in Figure 4 of the 
service bulletin.
    (n) Perform the inspections specified in paragraph (m) of this 
AD at the later of the times specified in paragraphs (n)(1) and 
(n)(2) of this AD.
    (1) Within 3,000 flight cycles or 24 months, whichever occurs 
first, after accomplishment of the modification required by 
paragraph (j) of this AD.
    (2) Within 600 flight cycles or 100 days, whichever occurs 
first, after the effective date of this AD.

Follow-on/Corrective Actions

    (o) If no cracking is found during any inspection required by 
paragraph (m) of this AD: Repeat the inspections specified in 
paragraph (m) of this AD thereafter within the applicable intervals 
specified in paragraph 1.E., Table 1, of Boeing Service Bulletin 
727-54A0010, Revision 6, dated August 23, 2001. Accomplishment of 
the modification specified in paragraph (j) of this AD does not 
terminate the requirement to repetitively perform the post-
modification inspections specified in Part III of the service 
bulletin.
    (p) If any cracking is detected during any inspection required 
by paragraph (m) of this AD: Before further flight, repair in 
accordance with Boeing Service Bulletin 727-54A0010, Revision 6, 
dated August 23, 2001, excluding the Evaluation Form; except as 
required by paragraph (q) of this AD.

Exception to Corrective Actions

    (q) Where Boeing Service Bulletin 727-54A0010, Revision 6, dated 
August 23, 2001, specifies to contact Boeing for appropriate action: 
Before further flight, replace or repair the fitting per a method 
approved by the Manager, Seattle ACO; or per data meeting the type 
certification basis of the airplane approved by a Boeing Company DER 
who has been authorized by the Manager, Seattle ACO, to make such 
findings. For a repair method to be approved, the approval must 
refer specifically to this AD.

    Note 6: Boeing Service Bulletin 727-54A0010, Revision 6, dated 
August 23, 2001, recommends that operators report inspection results 
to the manufacturer; however, this AD does not contain such a 
reporting requirement.

Spare Parts

    (r) As of the effective date of this AD, no person may install a 
forward support fitting on any airplane, unless it has been 
inspected and modified, as applicable, in accordance with the 
requirements of this AD.

Alternative Methods of Compliance

    (s)(1) 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

[[Page 23235]]

Maintenance Inspector, who may add comments and then send it to the 
Manager, Seattle ACO.
    (2) Alternative methods of compliance previously approved 
according to AD 97-05-08 are acceptable for compliance with the 
corresponding requirements of this AD.

    Note 7: 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

    (t) Special flight permits may be issued according to 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.

    Issued in Renton, Washington, on April 25, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-10728 Filed 4-30-03; 8:45 am]
BILLING CODE 4910-13-P