[Federal Register Volume 68, Number 1 (Thursday, January 2, 2003)]
[Rules and Regulations]
[Pages 5-10]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-32881]


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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; correction.

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SUMMARY: This document corrects information in an existing 
airworthiness directive (AD) that applies to all McDonnell Douglas 
Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83

[[Page 6]]

(MD-83), DC-9-87 (MD-87), and MD-88 airplanes. That AD 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. That AD also requires disabling the anti-ice systems for the 
upper wing surface on certain airplanes. This document corrects 
incorrect paragraph references in two paragraphs. This correction is 
necessary to ensure that operators are aware of an incorrect reference 
in paragraphs (1)(2)(i) and (1)(2)(ii) of the existing AD.

DATES: Effective November 8, 2002.
    In incorporation by reference of certain publications listed in the 
regulations was approved previously by the Director of the Federal 
Register as of November 8, 2002, (67 FR 65298, October 24, 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).
    The comment period specified for the existing rule remains December 
23, 2002.

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) 227p-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 October 9, 2002, the Federal Aviation 
Administration (FAA) issued AD 2002-21-06, amendment 39-12912 (67 FR 
65298, October 24, 2002), which applies 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 AD requires revisions to the Airplane Flight 
Manual; installation of inspection aids on the wing upper surfaces; 
and, among actions, 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. That AD also 
requires disabling the anti-ice systems for the upper wing surface on 
certain airplanes. The actions requires by that AD are intended to 
prevent ice ingestion 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.

Need for the Correction

    The FAA notes that an inadvertent transpositions of paragraph 
identifiers occurred in paragraphs (1)(2)(i) and (1)(2)(ii) of AD 2002-
21-06. Paragraph (1) of that AD specifies information regarding 
alternative methods of compliance (AMOCs) for the requirements of that 
AD. Specifically, paragraph (1)(2)(i) states that 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 that AD. While 
paragraph (i)(2) of that AD is a correct reference, the reference to 
paragraph (b) is incorrect and should read paragraph ``(c)'' of the AD. 
Conversely, paragraph (1)(2)(ii) of that AD states that 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 the 
AD. While paragraph (i)(3) of that AD is correct reference, the 
reference to paragraph (c) is incorrect and should read paragraph 
``(b)'' of that AD.
    The FAA has determined that a correction to AD 2002-21-06 is 
necessary to revise incorrect paragraph references in paragraphs 
(1)(2)(i) and (1)(2)(ii) of that AD. This correction specifies the 
appropriate paragraphs for which the specified AMOCs apply.

Correction of Publication

    This document corrects the errors and correctly adds the AD as an 
amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 
39.13).
    The AD is reprinted in its entirety for the convenience of affected 
operators. The effective date of the AD remains November 8, 2002.
    Since this action only corrects two incorrect paragraph references 
for AMOCs, it has no adverse economic impact and imposes no additional 
burden on any person. Therefore, the FAA has determined that notice and 
public procedures are unnecessary.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Correction

    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  [Corrected]

    2. Section 39.13 is amended by correctly adding the following 
airworthiness directive (AD):

2002-21-06 McDonnell Douglas: Amendment 39-12912. Docket 2002-NM-
216-AD.

    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 ara 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 (1)(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.
    The prevent damage to the upper wing skin surface and its 
structure, due to prolonges 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,

[[Page 7]]

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.
    (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 n 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

[[Page 8]]

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., SA 6042NM, 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.

``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 lien; 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 different 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

[[Page 9]]

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)(1), (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., SA60242NM, 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 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)

    (1)(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 though Revision 7, is approved as an AMOC with paragraphs (c) 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 (b) 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 Bulletin  Original..........  August 8, 2002.
 109XXXX-30-38.
McDonnell Douglas Alert Service   Original..........  September 22,
 Bulletin MD80-30A087.                                 1997.
McDonnell Douglas Service         Original..........  September 18,
 Bulletin 30-59.                                       1989.
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.
------------------------------------------------------------------------


[[Page 10]]

    (1) The incorporation by reference of Honeywell Alert Service 
Bulletin 109XXXX-30-38, dated August 8, 2002, was approved 
previously by the Director of the Federal Register as of November 8, 
2002 (67 FR 65298, October 24, 2002).
    (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 January1 7, 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) The effective date of this amendment remains November 8, 
2002.

    Issued in Renton, Washington, on December 23, 2002.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-32881 Filed 12-31-02; 8:45 am]
BILLING CODE 4910-13-U