Federal Register / Vol. 66, No. 112 / Monday, June 11, 2001 / Rules and Regulations 31121

finds that approval is consistent with

safety and soundness. To be deemed

complete, the application must include:

(1) Certification that the bank is an

‘‘eligible bank’’ as defined in § 32.2(i);

(2) Citations to relevant State laws or

regulations;

(3) A copy of a written resolution by

a majority of the bank’s board of

directors approving the use of the limits

provided in paragraphs (a)(1) and (2) of

this section, and confirming the terms

and conditions for use of this lending

authority; and

(4) A description of how the board

will exercise its continuing

responsibility to oversee the use of this

lending authority.

(c) Duration of approval. Except as

provided in § 32.7(d), a bank that has

received OCC approval may continue to

make loans and extensions of credit

under the special lending limits in

paragraphs (a)(1) and (2) of this section

until the date three years after

September 10, 2001, provided the bank

remains an ‘‘eligible bank.’’

(d) Discretionary termination of

authority. The OCC may rescind a

bank’s authority to use the special

lending limits in paragraphs (a)(1) and

(2) of this section based upon concerns

about credit quality, undue

concentrations in the bank’s portfolio of

residential or small business loans, or

concerns about the bank’s overall credit

risk management systems and controls.

The bank must cease making new loans

or extensions of credit in reliance on the

special limits upon receipt of written

notice from the OCC that its authority

has been rescinded.

(e) Duration of pilot program. The

pilot program will terminate on June 11,

2004, unless it is terminated sooner by

the OCC.

(f) Existing loans. Any loans or

extensions of credit made by a bank

under the special lending limits in

paragraphs (a)(1) and (2) of this section,

that were in compliance with this

section when made, will not be deemed

a lending limit violation and will not be

treated as nonconforming under § 32.6.

Dated: May 31, 2001.

John D. Hawke, Jr.,

Comptroller of the Currency.

[FR Doc. 01–14529 Filed 6–8–01; 8:45 am]

BILLING CODE 4810–33–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–326–AD; Amendment

39–12163; AD 2001–06–16]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–9–80 Series

Airplanes and Model MD–88 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This document corrects

information in an existing airworthiness

directive (AD) that applies to all

McDonnell Douglas Model DC–9–80

series airplanes and Model MD–88

airplanes. That AD currently requires

revisions to the Airplane Flight Manual

(AFM) and installation of inspection

aids on the wing upper surfaces. That

AD also requires, 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

document corrects an incorrect

paragraph reference. This correction is

necessary to ensure that operators are

aware of an incorrect paragraph

reference in paragraph (d)(2)(ii)(A) of

the existing AD.

DATES: Effective May 7, 2001.

The incorporation by reference of

certain publications listed in the

regulations was approved previously by

the Director of the Federal Register as of

January 17, 1992 (57 FR 2014,

November 12, 1998).

The incorporation by reference of

certain other publications 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).

ADDRESSES: 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

(800–0024). This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

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.

FOR FURTHER INFORMATION CONTACT:

Albert Lam, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California

90712–4137; telephone (562) 627–5346;

fax (562) 627–5210.

SUPPLEMENTARY INFORMATION: On March

23, 2001, the Federal Aviation

Administration (FAA) issued AD 2001–

06–16, amendment 39–12163 (66 FR

17499, April 2, 2001), which applies to

all McDonnell Douglas Model DC–9–80

series airplanes and Model MD–88

airplanes. That AD supersedes an

existing AD to continue to require

revisions to the Airplane Flight Manual

(AFM) and installation of inspection

aids on the wing upper surfaces. That

AD also requires, 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 was prompted by incidents in which

ice accumulation on the wing upper

surfaces shed into the engines during

takeoff. The actions required by that AD

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.

Need for the Correction

As discussed in the preamble of AD

2001–06–16, the FAA deleted paragraph

(f)(1)(iii) and other subparagraphs of the

supplemental NPRM from the final rule.

Although we deleted these paragraphs,

we inadvertently did not update an

associated paragraph reference in

paragraph (d)(2)(ii)(A) of AD 2001–06–

16. As a result, paragraph (d)(2)(ii)(A)

incorrectly references paragraph

(f)(1)(iii)(B) for installation of an

equipment protective device (EPD); the

correct reference is paragraph (f)(2)(i).

The FAA has determined that a

correction to AD 2001–06–16 is

necessary to revise an incorrect

paragraph reference in paragraph

(d)(2)(ii)(A) of AD 2001–06–16.

Correction of Publication

This document corrects the error and

correctly adds the AD as an amendment

to § 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

May 7, 2001.

31122 Federal Register / Vol. 66, No. 112 / Monday, June 11, 2001 / Rules and Regulations

Since this action only corrects an

incorrect paragraph reference, 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.

§ 39.13 [Corrected]

2. Section 39.13 is amended by

correctly adding the following

airworthiness directive (AD):

2001–06–16 McDonnell Douglas:

Amendment 39–12163. Docket 98–NM–

326–AD. Supersedes AD 92–03–02,

Amendment 39–8156.

Applicability: All Model DC–9–81, –82,

–83, and –87 series airplanes; and Model

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 (i)(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 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, accomplish the following:

Restatement of Requirements of AD 92–03–

02

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

§§ 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.

New Requirements of This AD

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 the effective date of this AD:

Within 60 days after the effective date of this

AD, 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

Federal Register / Vol. 66, No. 112 / Monday, June 11, 2001 / Rules and Regulations 31123

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 the effective date of

this AD, 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 ServiceBulletin 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.

Note 6: Installation of an overwing heater

blanket system in accordance with

AlliedSignal STC SA6061NM, is an approved

means of compliance with the requirements

of paragraph (f)(2)(ii) of this AD.

(iii) Install an FAA-approved primary

upper wing ice detection system in

accordance with a method approved by the

Manager, Los Angeles ACO.

Note 7: Boeing (McDonnell Douglas) has

received FAA approval of an acceptable

primary upper wing ice detection system.

This modification has been assigned a Boeing

(McDonnell Douglas) service bulletin number

but, at this time, no service bulletin is

available.

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]’’

(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

§§ 91.527 and 121.629. [END OF NOTE]’’

(2) Revise the CDL Appendix of the FAAapproved 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

31124 Federal Register / Vol. 66, No. 112 / Monday, June 11, 2001 / Rules and Regulations

(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.

Alternative Methods of Compliance

(i)(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 alternative methods of

compliance (AMOC) were approved

previously per AD 92–03–02, amendment

39–8156, and are approved as AMOC’s 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 paragraph (b) of this AD.

(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 paragraph (c) of

this AD.

Note 8: 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

(j) Special flight permits may be issued in

accordance with §§ 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

(k) The actions required by paragraphs (c),

(d), (e), (f)(1), and (h)(3) of this AD shall be

done in accordance with the applicable

service document identified in Table 1 of this

AD.

TABLE 1.—REFERENCED SERVICE

DOCUMENTS

Service document Revision

level Date

McDonnell Douglas

Service Bulletin

30–59.

Original ... Sept. 18,

1989.

McDonnell Douglas

Service Bulletin

30–59.

1 ............. Jan. 5,

1990.

McDonnell Douglas

Service Bulletin

30–59.

2 ............. Aug. 15,

1990.

McDonnell Douglas

Alert Service Bulletin MD80–

30A087.

Original ... Sept. 22,

1997.

McDonnell Douglas

Service Bulletin

MD80–30–090.

Original ... Oct. 19,

1999.

McDonnell Douglas

Service Bulletin

MD80–30–078.

01 ........... Apr. 8,

1997.

McDonnell Douglas

Service Bulletin

MD80–30–071.

02 ........... Feb. 6,

1996

(1) 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).

(2) 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).

(3) 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

(1) The effective date of this amendment

remains May 7, 2001.

Issued in Renton, Washington, on May 30,

2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–14040 Filed 6–8–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–283–AD; Amendment

39–12248; AD 2001–11–06]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Boeing Model 747–

100 series airplanes, that currently

requires repetitive inspections to detect

cracking of the outer chord of the body

station (BS) 1480 upper and lower

bulkhead and longeron splice fitting;

repair, if necessary; and modification of

the skin splice plate, the outer chord

splice fitting, and the stringer interface

of the lower bulkhead, if necessary. This

amendment revises the applicability of

the existing AD to add additional

airplanes, requires accomplishment of

previously optional inspections and

clarifies those inspections, extends

certain compliance times, and requires

additional work in certain areas. This

amendment is prompted by reports that

fatigue cracking has been found in the

outer chord of the BS 1480 bulkhead at

the overwing longeron splice on

airplanes not subject to the existing AD.

The actions specified by this AD are

intended to detect and correct fatigue

cracking of the skin, splice fittings,

bulkhead web, and outer chord of the

BS 1480 upper and lower bulkhead and

longeron splice fitting, which could

result in reduced structural integrity of

the fuselage and the inability to carry

limit load.

DATES: Effective July 16, 2001.

The incorporation by reference of

Boeing Alert Service Bulletin 747–

53A2390, Revision 1; including

Appendices A, B, C, and D; dated July

6, 2000; as listed in the regulations, is

approved by the Director of the Federal

Register as of July 16, 2001.

The incorporation by reference of

Boeing Alert Service Bulletin 747–

53A2390, dated July 31, 1997, as listed

in the regulations, was approved

previously by the Director of the Federal

Register as of October 7, 1998 (63 FR

50508, September 22, 1998).

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,