AD 67-30-05

AD Final Rules - DRS_67-30-05.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
67-30-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-9 Series Airplanes
Subject:
Battery Charger
Status:
Current
Citation:
(Federal Register: November 9, 1967)
Citation Publish Date:
11/09/1967
Effective Date:
12/19/1967
Make:
The Boeing Company
Model:
DC-9-11 | DC-9-12 | DC-9-13 | DC-9-14 | DC-9-15 | DC-9-15F | DC-9-21 | DC-9-31 | DC-9-32 | DC-9-32 (...Show more
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 67-30-05
CITATION:   [Federal Register: November 9, 1967]

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-505

AD NUMBER:   67-30-05

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-9 Series Airplanes



ACTION:  

SUMMARY:  

DATES:   Effective December 19, 1967.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
67-30-05 MCDONNELL DOUGLAS: Amdt. 39-505 Part 39 Federal Register November 9, 1967. Applies to Model DC-9 Series Airplanes.

Compliance required as indicated.

Due to at least three reports of malfunctions in the battery charger installed in DC-9 airplanes that have resulted in smoke and fire in the electrical compartment, accomplish the following:

1. Within 10 hours' time in service after the effective date of this AD:

A. Inspect the battery charger, P/N 263-40061-01 and inspect and service each battery in the electrical compartment in accordance with Paragraphs 1, 2 and 3 of the "Inspection Procedures for Aircraft" section of a wire dated 10-19-67, constituting McDonnell Douglas DC-9 Alert Service Bulletin A-24-26, or by a method approved by the Chief, Aircraft Engineering Division, FAA, Western Region:

B. Deactivate circuit breakers normally coded K7, K8, and K9, titled battery charger and transfer relay (20 AMP, left bus) and secure in the open position, or remove and stow wires P32A14C, P33A14B, and P34A-14A at the circuit breaker:

C. Placard circuit breakers K7, K8, and K9 to indicate that they are deactivated:

D. Unless already accomplished in accordance with Paragraph 5 of the "Inspection Procedures for Aircraft" section of the Service Bulletin referenced in this Paragraph, place an operating limitation in the form of a placard in the vicinity of the APU start switch stating: "Operating Limitation, Do not start APU electrically inflight": and

E. Unless already accomplished in accordance with Paragraph 5 of the "Inspection Procedures for Aircraft" section of the Service Bulletin referenced in this Paragraph, place an operating limitation in the form of a placard in the cockpit in clear view of the pilot and copilot, stating: "Operating Limitation, Do not ground start APU after battery charger circuit breakers are opened (pulled) prior to takeoff."

2. If an inspection specified in Paragraph 1 of this AD reveals evidence of overheating, cracking, or other abnormal appearance of the battery charger (including the flag lugs and positive ceramic stud build-up and solder-joint on the inside and outside of the charger on the filter, and the solder-joints to chassis), replace before further flight.

3. The following operating limitations are prescribed for all affected airplanes:

A. Immediately prior to start of each taxi:

i. Determine that the battery charger is operating in the pulsing mode.

ii. Pull circuit breakers U21, W21, and X24 in immediate succession to deactivate the batter charger.

iii. Enter the electrical compartment and inspect the battery charger and adjacent vicinity to determine that the charger has been operating satisfactorily as evidence by a lack of smoke. (May be accomplished by ground personnel.)

B. After parking close (push in) circuit breakers U21, W21, and X21 in immediate succession.

NOTE No. 1: The APU may be started after landing and during taxi to the ramp.

NOTE No. 2: The APU may be windmill started in flight in the event of a complete in-flight loss of electrical power.

The operating limitations specified in Subparagraphs A and B of this Paragraph must be placed in the aircraft in the form of a placard in clear view of the pilot. For the purpose of this AD, any document (including a pilot check list) including these limitations constitutes a "placard" within the meaning of this Paragraph.

4. Compliance with Paragraphs 1 and 3 of this AD is no longer required, and the operating limitations prescribed in those Paragraphs may be removed upon:

A. Accomplishing the modifications specified in the "Accomplishment Instructions" sections of McDonnell Douglas DC-9 Service Bulletin Nos. 24-25 dated December 1, 1967 (or later FAA-approved revision), 24-27 dated December 1, 1967 (or later FAA-approved revision), 25-97 dated November 10, 1967 (or later FAA-approved revision); and

B. Removing FAA-approved revisions dated May 3, 1967, and incorporating FAA-approved revisions dated December 1, 1967, to the Emergency Procedures Section of the FAA-approved DC-9 Series 10 Airplane Flight Manual (Douglas Report DAC-32999) or the FAA-approved DC-9 Series 30 Airplane Flight Manual (Douglas Report DAC-33530), as appropriate, under the heading of "Electrical Smoke of Unknown Origin" Phase III.

This amendment effective December 19, 1967.


FOOTER: