Airworthiness Directives; McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 Airplanes

[Federal Register Volume 67, Number 206 (Thursday, October 24, 2002)]
[Rules and Regulations]
[Pages 65298-65303]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-26480]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-216-AD; Amendment 39-12912; AD 2002-21-06]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-9-81 (MD-
81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to all McDonnell Douglas Model DC-9-81 (MD-81), DC-9-
82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes, that 
currently requires revisions to the Airplane Flight Manual; 
installation of inspection aids on the wing upper surfaces; and, among 
other actions, installation of an overwing heater blanket system or 
primary upper wing ice detection system, and installation of a heater 
protection panel or an equipment protection device on certain overwing 
heater blanket systems. This amendment retains those requirements and 
adds a requirement to disable the anti-ice systems for the upper wing 
surface on certain airplanes. The actions specified in this AD are 
intended to prevent ingestion of ice into one or both engines and 
consequent loss of thrust from one or both engines; and damage to the 
upper wing skin surface and its structure, due to prolonged short-
circuit electrical arcing of certain anti-ice systems.

DATES: Effective November 8, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 8, 2002.
    The incorporation by reference of certain publications, as listed 
in the regulations, was approved previously by the Director of the 
Federal Register as January 17, 1992 (57 FR 2014, January 17, 1992).
    The incorporation by reference of certain other publications, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of May 7, 2001 (66 FR 17499, April 2, 2001).
    Comments for inclusion in the Rules Docket must be received on or 
before December 23, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-216-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-216-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 Aircraft Group, Long Beach Division, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024). This information may be examined 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or at the FAA, Los Angeles Aircraft

[[Page 65299]]

Certification Office, 3960 Paramount Boulevard, Lakewood, California; 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW., Suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Technical Information: Daniel Bui, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130L, FAA, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712-4137; telephone (562) 627-5339; fax (562) 
627-5210.
    Other Information: Judy Golder, Airworthiness Directive Technical 
Editor/Writer; telephone (425) 687-4241, fax (425) 227-1232. Questions 
or comments may also be sent via the Internet using the following 
address: [email protected]. Questions or comments sent via the 
Internet as attached electronic files must be formatted in Microsoft 
Word 97 for Windows or ASCII text.

SUPPLEMENTARY INFORMATION: On May 30, 2001, the FAA issued AD 2001-06-
16 COR, amendment 39-12163 (66 FR 31121, June 11, 2001), applicable to 
all McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 
(MD-83), DC-9-87 (MD-87), and MD-88 airplanes. That amendment corrected 
an incorrect paragraph reference in AD 2001-06-16, amendment 39-12163 
(66 FR 17499, April 2, 2001). AD 2001-06-16 was prompted by incidents 
in which ice accumulation on the wing upper surfaces shed into the 
engines during takeoff. AD 2001-06-16 COR requires revisions to the 
Airplane Flight Manual (AFM); installation of inspection aids on the 
wing upper surfaces; and, among other actions, installation of an 
overwing heater blanket system or primary upper wing ice detection 
system, and installation of a heater protection panel or an equipment 
protection device on certain overwing heater blanket systems. The 
actions required by AD 2002-06-16 COR are intended to prevent ice 
accumulation on the wing upper surfaces, which could result in 
ingestion of ice into one or both engines and consequent loss of thrust 
from one or both engines.

Actions Since Issuance of Previous Rule

    Since the issuance of AD 2001-06-16 COR, the FAA has received 
reports of short-circuit electrical arcing at the upper wing interface 
unit and on the wing upper surface of the Honeywell Anti-Ice System, 
which was installed per Supplemental Type Certificate (STC) SA6061NM. 
During the investigation of one incident, a burn-through hole resulting 
from a high energy electrical short was observed on the cover plate of 
the interface unit. Investigation of another incident revealed a small 
pitting hole on the upper wing surface near the heater. Wire chafing 
appears to have caused the over-wing heater blanket system to short 
circuit. This condition, if not corrected, could cause prolonged short-
circuit electrical arcing of the anti-ice system, which could result in 
damage to the upper wing skin surface and its structure.

Issuance of New Service Information

    Honeywell has issued Alert Service Bulletin, 109XXXX-30-38, dated 
August 8, 2002, which describes procedures to disable the upper wing 
surface anti-ice system for those airplanes on which STC SA6061NM has 
been installed. The Honeywell anti-ice system specified in that service 
bulletin is identical to the Allied Signal overwing heater blanket 
system referred to in AD 2001-06-16 COR.

Explanation of Requirements of Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of this same type design, this AD 
supersedes AD 2001-06-16 COR. This AD continues to require revisions to 
the Airplane Flight Manual (AFM); installation of inspection aids on 
the wing upper surfaces; and, among other actions, installation of an 
overwing heater blanket system or primary upper wing ice detection 
system, and installation of a heater protection panel or an equipment 
protection device on certain overwing heater blanket systems. This AD 
also requires disabling the anti-ice systems for the upper wing surface 
of airplanes equipped with Honeywell Anti-Ice Systems installed per STC 
SA6061NM, per the service bulletin described previously.

Explanation of Change to Applicability

    The FAA has revised the applicability of the AD 2002-06-16 COR to 
identify model designations as published in the most recent type 
certificate date sheet for the affected models.

Removal of Note 6 From AD 2001-06-16 COR

    Note 6 of AD 2001-06-16 COR states that installation of an overwing 
heater blanket system per Allied Signal STC SA6061NM (also known and 
specified in this AD as a Honeywell anti-ice system installed per STC 
SA6061NM) is an approved means of compliance with the requirements of 
paragraph (f)(2)(ii) of that AD. Since this AD requires disabling the 
system installed per STC SA6061NM, the FAA has removed the wording of 
the previous Note 6 from this AD, and renumbered the notes accordingly.

Interim Action

    This is considered to be interim action. Honeywell has advised that 
it currently is developing a modification that will address 
reactivating the anti-ice system that will be disabled per the 
requirements of this AD. Once this modification is developed, approved, 
and available, the FAA may consider additional rulemaking.

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 
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

[[Page 65300]]

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 2002-NM-216-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 removing amendment AD 2001-06-16 
COR, 39-12163 (66 FR 31121, June 11, 2001), and by adding a new 
airworthiness directive (AD), amendment 39-12912, to read as follows:

2002-21-06 McDonnell Douglas: Amendment 39-12912. Docket 2002-NM-
216-AD. Supersedes AD 2001-06-16 COR, Amendment 39-12163.
    Applicability: All Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-
83 (MD-83), DC-9-87 (MD-87), and MD-88 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 (l)(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 damage to the upper wing skin surface and its 
structure, due to prolonged short-circuit electrical arcing of the 
anti-ice system; accomplish the following:

Restatement of AD 2001-06-16 COR

Airplane Flight Manual Revision

    (a) Within 10 days after January 17, 1992 (the effective date of 
AD 92-03-02, amendment 39-8156), revise the Limitations Section of 
the FAA-approved Airplane Flight Manual (AFM) to include the 
following. This may be accomplished by inserting a copy of this AD 
in the AFM.

``Ice on Wing Upper Surfaces

CAUTION

    Ice shedding from the wing upper surface during takeoff can 
cause severe damage to one or both engines, leading to surge, 
vibration, and complete thrust loss. The formation of ice can occur 
on wing surfaces during exposure of the airplane to normal icing 
conditions. Clear ice can also occur on the wing upper surfaces when 
cold-soaked fuel is in the main wing fuel tanks, and the airplane is 
exposed to conditions of high humidity, rain, drizzle, or fog at 
ambient temperatures well above freezing. Often, the ice 
accumulation is clear and difficult to detect visually. The ice 
forms most frequently on the inboard, aft corner of the main wing 
tanks. [END OF CAUTIONARY NOTE]
    The wing upper surfaces must be physically checked for ice when 
the airplane has been exposed to conditions conducive to ice 
formation. Takeoff may not be initiated unless the flight crew 
verifies that a visual check and a physical (hands-on) check of the 
wing upper surfaces have been accomplished, and that the wing is 
clear of ice accumulation when any of the following conditions 
occur:
    (1) When the ambient temperature is less than 50 degrees F and 
high humidity or visible moisture (rain, drizzle, sleet, snow, fog, 
etc.) is present;
    (2) When frost or ice is present on the lower surface of either 
wing;
    (3) After completion of de-icing.
    When inspection aids (i.e. tufts, decals, mount pads, painted 
symbols, and paint stripes) are installed in accordance with 
McDonnell Douglas MD-80 Service Bulletin 30-59, the physical check 
may be made by assuring that all installed tufts move freely.

NOTE

    This limitation does not relieve the requirement that aircraft 
surfaces are free of frost, snow, and ice accumulation, as required 
by Federal Aviation Regulations Sections 91.527 and 121.629. [END OF 
NOTE]''

AFM Configuration Deviation List Revision

    (b) Within 10 days after January 17, 1992, revise the 
Configuration Deviation List (CDL) Appendix of the FAA-approved AFM 
to include the following. This may be accomplished by inserting a 
copy of this AD in the AFM.

``30-80-01 Triangular Decal and Tuft Assemblies

    Up to two (2) decals or tufts per side may be missing, provided:
    (a) At least one decal and tuft on each side is located along 
the aft spar line; and
    (b) The tufts are used for performing the physical check to 
determine that the upper wing is free of ice by observing that the 
tufts move freely.
    Up to eight (8) decals and/or tufts may be missing, provided:
    (a) Takeoff may not be initiated unless the flight crew verifies 
that a physical (hands-on) check is made of the upper wing in the 
location of the missing decals and/or tufts to assure that there is 
no ice on the wing when icing conditions exist;

OR

    (b) When the ambient temperature is more than 50 degrees F.''

Installation of Inspection Aids

    (c) Within 30 days after January 17, 1992, install inspection 
aids (i.e., tufts, decals, mount pads, painted symbols, and paint 
stripes) on the inboard side of the wings' upper surfaces, in 
accordance with McDonnell Douglas Service Bulletin 30-59, dated 
September 18, 1989; Revision 1, dated January 5, 1990; or Revision 
2, dated August 15, 1990.

Repetitive Tests and One-Time Inspection

    (d) For airplanes on which an overwing heater blanket system was 
installed without installation of a heater protection panel (HPP) or 
an equipment protection device (EPD) prior to May 7, 2001 (the 
effective date of 2001-06-16 COR, amendment 39-12163): Within 60 
days days after May 7, 2001, accomplish the actions specified in 
paragraph (d)(1) or (d)(2) of this AD, as applicable.

[[Page 65301]]

    (1) For airplanes on which the overwing heater blanket system 
was installed in accordance with McDonnell Douglas Service Bulletin 
MD80-30-071, Revision 02, dated February 6, 1996; or McDonnell 
Douglas Service Bulletin MD80-30-078, Revision 01, dated April 8, 
1997: Accomplish paragraphs (d)(1)(i) and (d)(1)(ii) of this AD.
    (i) Remove secondary access covers, and perform a one-time 
detailed visual inspection to detect discrepancies (mechanical 
damage or punctures in the upper skin of the blanket, prying damage 
on the panel, and fuel leakage) of the overwing heater blanket, in 
accordance with McDonnell Douglas Alert Service Bulletin MD80-
30A087, dated September 22, 1997. And,
    (ii) Accomplish paragraph (d)(1)(ii)(A) or (d)(1)(ii)(B) of this 
AD.
    (A) Perform dielectric withstanding voltage and resistance tests 
in accordance with McDonnell Douglas Alert Service Bulletin MD80-
30A087, dated September 22, 1997. Repeat the tests thereafter at 
intervals not to exceed 150 days, until installation of an HPP in 
accordance with paragraph (f)(1)(i) or (f)(1)(ii) of this AD, as 
applicable.
    (B) Deactivate the overwing heater blanket system until 
accomplishment of dielectric withstanding voltage and resistance 
tests specified in paragraph (d)(1)(ii)(A). If the overwing heater 
blanket system is deactivated as provided by this paragraph, 
continue to accomplish the requirements of paragraphs (a), (b), and 
(c) of this AD.

    Note 2: 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.''

    (2) For airplanes on which the overwing heater blanket system 
was installed in accordance with TDG Aerospace, Inc., STC SA6042NM: 
Accomplish paragraphs (d)(2)(i) and (d)(2)(ii) of this AD.
    (i) Remove secondary access covers, and perform a one-time 
detailed visual inspection to detect discrepancies (mechanical 
damage or punctures in the upper skin of the blanket, prying damage 
on the panel, and fuel leakage) of the overwing heater blanket, in 
accordance with McDonnell Douglas Alert Service Bulletin MD80-
30A087, dated September 22, 1997. And,
    (ii) Accomplish paragraph (d)(2)(ii)(A) or (d)(2)(ii)(B) of this 
AD.
    (A) Perform dielectric withstanding voltage and resistance tests 
in accordance with McDonnell Douglas Alert Service Bulletin MD80-
30A087, dated September 22, 1997. Repeat the tests thereafter at 
intervals not to exceed 150 days, until installation of an EPD in 
accordance with paragraph (f)(2)(i) of this AD.
    (B) Deactivate overwing heater blanket system until 
accomplishment of dielectric withstanding voltage and resistance 
tests specified in paragraph (d)(2)(ii)(A). If the overwing heater 
blanket system is deactivated as provided by this paragraph, 
continue to accomplish the requirements of paragraphs (a), (b), and 
(c) of this AD.

Corrective Action

    (e) If any discrepancy is detected during any inspection or test 
performed in accordance with paragraph (d) of this AD, prior to 
further flight, repair or replace the affected heater blanket, in 
accordance with McDonnell Douglas Alert Service Bulletin MD80-
30A087, dated September 22, 1997; except as provided in paragraph 
(h) of this AD.

    Note 3: McDonnell Douglas Alert Service Bulletin MD80-30A087, 
dated September 22, 1997, references TDG Aerospace Document E95-451, 
Revision B, dated January 31, 1996, as an additional source of 
service information for accomplishment of repair or replacement of 
the overwing heater blanket.

Installation of Overwing Heater Blanket or Primary Upper Wing Ice 
Detection System

    (f) Within 3 years after May 7, 2001, do the requirements of 
either paragraph (f)(1) or (f)(2) of this AD.
    (1) Do the actions specified in paragraph (f)(1)(i) or 
(f)(1)(ii) of this AD, as applicable.
    (i) For airplanes listed in Group 1 in McDonnell Douglas Service 
Bulletin MD80-30-090, dated October 19, 1999: Install an overwing 
heater blanket system in accordance with McDonnell Douglas Service 
Bulletin MD80-30-071, Revision 02, dated February 6, 1996; and 
modify and reidentify the existing HPP in accordance with McDonnell 
Douglas Service Bulletin MD80-30-090. Modification of the existing 
HPP in accordance with this paragraph constitutes terminating action 
for the repetitive inspections required by (d)(1)(ii)(A) of this AD.
    (ii) For airplanes listed in Group 2 in McDonnell Douglas 
Service Bulletin MD80-30-090, dated October 19, 1999: Install an 
overwing heater blanket system in accordance with McDonnell Douglas 
Service Bulletin MD80-30-078, Revision 01, dated April 8, 1997; and 
install an HPP and associated wiring in accordance with McDonnell 
Douglas Service Bulletin MD80-30-090. Installation of an HPP and 
associated wiring in accordance with this paragraph constitutes 
terminating action for the repetitive inspections required by 
(d)(1)(ii)(A) of this AD.

    Note 4: For other airplanes, accomplishment of the requirements 
of paragraph (f)(1)(i) or (f)(1)(ii) of this AD may be acceptable 
per paragraph (i)(1) of this AD.

    (2) Accomplish the actions specified in either paragraph 
(f)(2)(i), (f)(2)(ii), or (f)(2)(iii) of this AD.
    (i) Install an overwing heater blanket system, and install an 
EPD that provides a circuit protection function to the overwing 
heater blanket, in accordance with a method approved by the Manager, 
Los Angeles Aircraft Certification Office (ACO), FAA. Installation 
of an EPD in accordance with this paragraph constitutes terminating 
action for the repetitive inspections required by (d)(2)(ii)(A) of 
this AD.

    Note 5: Installation of an overwing heater blanket system and 
installation of an EPD that provides a circuit protection function 
to the overwing heater blanket, in accordance with TDG Aerospace, 
Inc., SA6042NM, or TDG Master Drawing List (MDL) E93-104, Revision 
R, dated October 25, 2000; is an approved means of compliance with 
the requirements of paragraph (f)(2)(i) of this AD.

    (ii) Install an overwing heater blanket system in accordance 
with a method approved by the Manager, Los Angeles ACO.
    (iii) Install an FAA-approved primary upper wing ice detection 
system in accordance with a method approved by the Manager, Los 
Angeles ACO.

    Note 6: Boeing (McDonnell Douglas) has received FAA approval of 
a primary upper wing ice detection system that is considered to be 
an alternative method of compliance (AMOC) with the requirements of 
paragraph (f)(2)(iii) of this AD. Information concerning such AMOCs 
may be obtained from the Los Angeles ACO.

AFM Revision

    (g) Except as provided by paragraph (h) of this AD, prior to 
further flight after accomplishment of the installation required by 
paragraph (f)(1) or (f)(2) of this AD, revise the Limitations 
Section of the FAA-approved AFM to include the following. This may 
be accomplished by inserting a copy of this AD in the AFM. After 
accomplishment of the installation required by paragraph (f)(1) or 
(f)(2) of this AD and this AFM revision, the AFM revisions required 
by paragraphs (a) and (b) of this AD may be removed from the AFM, 
and the inspection aids required by paragraph (c) of this AD may be 
removed from the airplane.

``Ice on Wing Upper Surfaces

CAUTION

    Ice shedding from the wing upper surface during takeoff can 
cause severe damage to one or both engines, leading to surge, 
vibration, and complete thrust loss. The formation of ice can occur 
on wing surfaces during exposure of the airplane to normal icing 
conditions. Clear ice can also occur on the wing upper surfaces when 
cold-soaked fuel is in the main wing fuel tanks, and the airplane is 
exposed to conditions of high humidity, rain, drizzle, or fog at 
ambient temperatures well above freezing. Often, the ice 
accumulation is clear and difficult to detect visually. The ice 
forms most frequently on the inboard, aft corner of the main wing 
tanks. [END OF CAUTIONARY NOTE]''

MMEL Provision

    (h) An airplane may be operated with an inoperative overwing 
heater blanket or primary upper wing ice detection system for 10 
days per the Master Minimum Equipment List (MMEL), provided that the 
actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this 
AD are done before further flight.
    (1) Revise the Limitations Section of the FAA-approved AFM to 
include the following. This may be accomplished by inserting a copy 
of this AD in the AFM.

[[Page 65302]]

``Ice on Wing Upper Surfaces

CAUTION

    The wing upper surfaces must be physically checked for ice when 
the airplane has been exposed to conditions conducive to ice 
formation. Takeoff may not be initiated unless the flight crew 
verifies that a visual check and a physical (hands-on) check of the 
wing upper surfaces have been accomplished, and that the wing is 
clear of ice accumulation when any of the following conditions 
occur:
    (1) When the ambient temperature is less than 50 degrees F and 
high humidity or visible moisture (rain, drizzle, sleet, snow, fog, 
etc.) is present;
    (2) When frost or ice is present on the lower surface of either 
wing;
    (3) After completion of de-icing.
    When inspection aids (i.e. tufts, decals, mount pads, painted 
symbols, and paint stripes) are installed in accordance with 
McDonnell Douglas MD-80 Service Bulletin 30-59, the physical check 
may be made by assuring that all installed tufts move freely.

NOTE

    This limitation does not relieve the requirement that aircraft 
surfaces are free of frost, snow, and ice accumulation, as required 
by Federal Aviation Regulations Sections 91.527 and 121.629. [END OF 
NOTE]''
    (2) Revise the CDL Appendix of the FAA-approved AFM to include 
the following. This may be accomplished by inserting a copy of this 
AD in the AFM.

``30-80-01 Triangular Decal and Tuft Assemblies

    Up to two (2) decals or tufts per side may be missing, provided:
    (a) At least one decal and tuft on each side is located along 
the aft spar line; and
    (b) The tufts are used for performing the physical check to 
determine that the upper wing is free of ice by observing that the 
tufts move freely.
    Up to eight (8) decals and/or tufts may be missing, provided:
    (a) Takeoff may not be initiated unless the flight crew verifies 
that a physical (hands-on) check is made of the upper wing in the 
location of the missing decals and/or tufts to assure that there is 
no ice on the wing when icing conditions exist;

OR

    (b) When the ambient temperature is more than 50 degrees F.''
    (3) Install inspection aids (i.e., tufts, decals, mount pads, 
painted symbols, and paint stripes) on the inboard side of the 
wings' upper surfaces, in accordance with McDonnell Douglas Service 
Bulletin 30-59, dated September 18, 1989; Revision 1, dated January 
5, 1990; or Revision 2, dated August 15, 1990.

New Requirements of This AD

    Note 7: The Honeywell Anti-Ice System specified in paragraphs 
(i), (j), and (k) of this AD, is also known and specified as an 
overwing heater blanket system installed in accordance with 
AlliedSignal Supplemental Type Certificate (STC) STC SA6061NM.

For Airplanes Equipped With a Honeywell Anti-Ice System Installed per 
STC SA6061NM

    (i) For airplanes equipped with a Honeywell Anti-Ice System 
installed per STC SA6061NM: Accomplish the actions specified in 
paragraphs (i)(1), (i)(2), (i)(3), and (i)(4) of this AD, at the 
times specified in those paragraphs.
    (1) Within 72 hours after the effective date of this AD, disable 
the Honeywell Anti-Ice System installed per STC SA6061NM, per 
Honeywell Alert Service Bulletin 109XXXX-30-38, dated August 8, 
2002.
    (2) Within 72 hours after the effective date of this AD, revise 
the Limitations Section of the FAA-approved AFM to include the 
following (this may be accomplished by inserting a copy of this AD 
in the AFM):

``Ice on Wing Upper Surfaces

CAUTION

    Ice shedding from the wing upper surface during takeoff can 
cause severe damage to one or both engines, leading to surge, 
vibration, and complete thrust loss. The formation of ice can occur 
on wing surfaces during exposure of the airplane to normal icing 
conditions. Clear ice can also occur on the wing upper surfaces when 
cold-soaked fuel is in the main wing fuel tanks, and the airplane is 
exposed to conditions of high humidity, rain, drizzle, or fog at 
ambient temperatures well above freezing. Often, the ice 
accumulation is clear and difficult to detect visually. The ice 
forms most frequently on the inboard, aft corner of the main wing 
tanks. [END OF CAUTIONARY NOTE]
    The wing upper surfaces must be physically checked for ice when 
the airplane has been exposed to conditions conducive to ice 
formation. Takeoff may not be initiated unless the flight crew 
verifies that a visual check and a physical (hands-on) check of the 
wing upper surfaces have been accomplished, and that the wing is 
clear of ice accumulation when any of the following conditions 
occur:
    (1) When the ambient temperature is less than 50 degrees F and 
high humidity or visible moisture (rain, drizzle, sleet, snow, fog, 
etc.) is present;
    (2) When frost or ice is present on the lower surface of either 
wing;
    (3) After completion of de-icing.
    When inspection aids (i.e. tufts, decals, mount pads, painted 
symbols, and paint stripes) are installed in accordance with 
McDonnell Douglas MD-80 Service Bulletin 30-59, the physical check 
may be made by assuring that all installed tufts move freely.

NOTE

    This limitation does not relieve the requirement that aircraft 
surfaces are free of frost, snow, and ice accumulation, as required 
by Federal Aviation Regulations Sections 91.527 and 121.629. [END OF 
NOTE]''

AFM Configuration Deviation List Revision

    (3) Within 72 hours after the effective date of this AD, revise 
the CDL Appendix of the FAA-approved AFM to include the following 
(this may be accomplished by inserting a copy of this AD in the 
AFM):

``30-80-01 Triangular Decal and Tuft Assemblies

    Up to two (2) decals or tufts per side may be missing, provided:
    (a) At least one decal and tuft on each side is located along 
the aft spar line; and
    (b) The tufts are used for performing the physical check to 
determine that the upper wing is free of ice by observing that the 
tufts move freely.
    Up to eight (8) decals and/or tufts may be missing, provided:
    (a) Takeoff may not be initiated unless the flight crew verifies 
that a physical (hands-on) check is made of the upper wing in the 
location of the missing decals and/or tufts to assure that there is 
no ice on the wing when icing conditions exist;

OR

    (b) When the ambient temperature is more than 50 degrees F.''

Installation of Inspection Aids

    (4) Within 30 days after the effective date of this AD, install 
inspection aids (i.e., tufts, decals, mount pads, painted symbols, 
and paint stripes) on the inboard side of the wings' upper surfaces, 
in accordance with McDonnell Douglas Service Bulletin 30-59, dated 
September 18, 1989; Revision 1, dated January 5, 1990; or Revision 
2, dated August 15, 1990.

    Note 8: Operators should note that certain AMOCs have been 
approved as acceptable methods of compliance with paragraph (i)(4) 
of this AD. Information concerning such AMOCs may be obtained from 
the Manager, Los Angeles ACO.

Installation of Overwing Heater Blanket or Primary Upper Wing Ice 
Detection System

    (j) For airplanes equipped with disabled Honeywell Anti-Ice 
Systems installed per STC SA6061NM: Within 3 years after May 7, 
2001, accomplish the requirements of paragraph (j)(l), (j)(2), or 
(j)(3) of this AD.
    (1) Install an overwing heater blanket system, and install an 
EPD that provides a circuit-protection function to the overwing 
heater blanket, in accordance with a method approved by the Manager, 
Los Angeles ACO, FAA.

    Note 9: Installation of an overwing heater blanket system and 
installation of an EPD that provides a circuit-protection function 
to the overwing heater blanket, in accordance with TDG Aerospace, 
Inc., SA6042NM, or TDG Master Drawing List (MDL) E93-104, Revision 
R, dated October 25, 2000; is an approved means of compliance with 
the requirements of paragraph (j)(1) of this AD.

    (2) Install an overwing heater blanket system in accordance with 
a method approved by the Manager, Los Angeles ACO.
    (3) Install an FAA-approved primary upper wing ice detection 
system in accordance with a method approved by the Manager, Los 
Angeles ACO.

    Note 10: Boeing (McDonnell Douglas) has received FAA approval of 
an acceptable primary upper wing ice detection system, which is 
considered to be an acceptable method of compliance with the 
requirements of paragraph (j)(3) of this AD when

[[Page 65303]]

accomplished in accordance with a method approved by the Manager, 
Los Angeles ACO.

AFM Revision

    (k)(1) For airplanes equipped with a disabled Honeywell Anti-Ice 
Systems installed per STC SA6061NM: Prior to further flight after 
accomplishment of the installation required by paragraph (j)(1), 
(j)(2), or (j)(3) of this AD, revise the Limitations Section of the 
FAA-approved AFM to include the following (this may be accomplished 
by inserting a copy of this AD in the AFM):

``Ice on Wing Upper Surfaces

CAUTION

    Ice shedding from the wing upper surface during takeoff can 
cause severe damage to one or both engines, leading to surge, 
vibration, and complete thrust loss. The formation of ice can occur 
on wing surfaces during exposure of the airplane to normal icing 
conditions. Clear ice can also occur on the wing upper surfaces when 
cold-soaked fuel is in the main wing fuel tanks, and the airplane is 
exposed to conditions of high humidity, rain, drizzle, or fog at 
ambient temperatures well above freezing. Often, the ice 
accumulation is clear and difficult to detect visually. The ice 
forms most frequently on the inboard, aft corner of the main wing 
tanks. [END OF CAUTIONARY NOTE]''
    (2) After accomplishment of the installation required by 
paragraph (j)(1) of this AD and this AFM revision, the AFM revisions 
and CDLs required by paragraphs (i)(2) and (i)(3) of this AD may be 
removed from the AFM, and the inspection aids required by paragraph 
(i)(4) of this AD may be removed from the airplane.

Alternative Methods of Compliance (AMOCs)

    (l)(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, Los Angeles 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, Los Angeles ACO.
    (2) The following AMOCs were approved previously per AD 92-03-
02, amendment 39-8156, and are approved as AMOCs with the indicated 
paragraphs of this AD:
    (i) Installation of a non-skid, striped triangular symbol per 
Option 5 of McDonnell Douglas Service Bulletin MD80-30-059, Revision 
4 through Revision 7, is approved as an AMOC with paragraphs (b) and 
(i)(2) of this AD; and
    (ii) Revision of the Configuration Deviation List (CDL) Appendix 
of the AFM by inserting a copy of CDL Appendix, Section I, Page 2A, 
dated March 10, 1993, into the AFM, is approved as an AMOC with 
paragraphs (c) and (i)(3) of this AD.

    Note 11: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

Special Flight Permits

    (m) Special flight permits may be issued in accordance with 
Sec. Sec.  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

    (n) Unless otherwise specified in this AD, the actions shall be 
done in accordance with the applicable service document identified 
in the following table:

------------------------------------------------------------------------
        Service Document          Revision Level            Date
------------------------------------------------------------------------
Honeywell Alert Service          Original........  August 8, 2002
 Bulletin 109XXXX-30-38.
--------------------------------
McDonnell Douglas Alert Service  Original........  September 22, 1997
 Bulletin MD80-30A087.
--------------------------------
McDonnell Douglas Service        Original........  September 18, 1989
 Bulletin 30-59.
--------------------------------
McDonnell Douglas Service        1...............  January 5, 1990
 Bulletin 30-59.
--------------------------------
McDonnell Douglas Service        2...............  August 15, 1990
 Bulletin 30-59.
--------------------------------
McDonnell Douglas Service        02..............  February 6, 1996
 Bulletin MD80-30-071.
--------------------------------
McDonnell Douglas Service        01..............  April 8, 1997
 Bulletin MD80-30-078.
--------------------------------
McDonnell Douglas Service        Original........  October 19, 1999
 Bulletin MD80-30-090.
------------------------------------------------------------------------

    (1) The incorporation by reference of Honeywell Alert Service 
Bulletin 109XXXX-30-38, dated August 8, 2002, is approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51.
    (2) The incorporation by reference of McDonnell Douglas Service 
Bulletin 30-59, dated September 18, 1989; McDonnell Douglas Service 
Bulletin 30-59, Revision 1, dated January 5, 1990; and McDonnell 
Douglas Service Bulletin 30-59, Revision 2, dated August 15, 1990; 
was approved previously by the Director of the Federal Register as 
of January 17, 1992 (57 FR 2014, January 17, 1992).
    (3) The incorporation by reference of the remaining service 
bulletins listed in Table 1 of this AD, was approved previously by 
the Director of the Federal Register as of May 7, 2001 (66 FR 17499, 
April 2, 2001).
    (4) Copies may be obtained from Boeing Commercial Aircraft 
Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, 
California 90846, Attention: Data and Service Management, Dept. C1-
L5A (D800-0024). Copies may be inspected at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 
at the FAA, Los Angeles Aircraft Certification Office, 3960 
Paramount Boulevard, Lakewood, California; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., Suite 700, 
Washington, DC.

Effective Date

    (o) This amendment becomes effective on November 8, 2002.

    Issued in Renton, Washington, on October 9, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-26480 Filed 10-23-02; 8:45 am]
BILLING CODE 4910-13-P

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